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Between 1997 and 1999, a Working Group on the feasibility of collaborative, multi-facility windtunnel testing for the validation of Computational Fluid Dynamics Codes (CFD) has established the following results: Windtunnel tests are the main source of CFD validation but all have specific bias errors. Testing of the same model in several facilities can better establish the level of uncertainty in windtunnel tests and hence help assess possible differences between CFD and windtunnel tests. The working group, after an initial inquiry, established the need for CFD validation for fighter aircraft, transport type aircraft, missiles and helicopters. Effort and cost can be controlled efficiently and would permit the improvement of CFD Codes for considerable cost saving in future developments.

Contents: ISTF Definition and Purpose; Verification and Validation (V & V); Description of the U.S. Navy's ISTF; The Air Combat Environment Test and Evaluation Facility (ACETEF); ACETEF V & V Process Development; and Summary.

Criteria are presented for selection of analytic models to represent waiting times due to queuing processes. An existing computer model by M.F. Neuts which assumes general nonparametric distributions of arrivals per unit time and service times for a single service was envisioned as best fulfilling requirements. Data obtained from Denver Stapleton Airport were applied to this model. Service times and arrival rates at an express baggage check facility, a security station, and a gate were used as inputs. Delay times corresponding to the observed arrival rates were recorded and compared to model outputs. Using the T-test, agreement was obtained at the 5 percent level of significance for the mean values of the first two facilities. Predictions of waiting time distribution, however, did not pass the Kolmogroff test at the same level of significance. Discrepancies are due to a lack of time resolution in arrival times and the application of this model to multiserver situations. (Author)

This report documents the CAORF Validation Studies conducted during CAORF acceptance testing and the early research experimentation phases. The specific areas of validation were hardware, information processing and behavioral validation. The validation testing to date indicates that: (1) The simulated ship reacts as its real world equivalent does. (2) The bridge equipment and visual scene react realistically to position and heading changes of ownship and traffic vessels. (3) The realism of the visual scene and radar display has been deemed satisfactory by experienced subjects. (4) Accuracy in distance estimation can be achieved by training. (5) Behavior on the CAORF bridge is similar to real-world behavior and provides valid research and training data. (Author)

The Radar Training Facility (RTF), part of the Federal Aviation Administration Academy located at the Oklahoma City Mike Monroney Aeronautical Center, is designed to identify, as early as possible, air traffic control specialists who do not demonstrate sufficient potential to perform at radar tasks at the journeyman level. An extensive initial validation effort involving design evaluation, implementation evaluation, and formative evaluation was performed to determine if the system was adequately designed from an educational point of view, if the measures employed were reliable, if the program had a proper concurrent relationship with nonradar Academy measures, and if the difficulty level was appropriate. While the program was not pass/fail during the study, a score of less than 70 was used to calculate experimental pass/fail rates. Data from the initial validation effort indicated that the system was educationally sufficient, reliabilities were low to moderate, the RTF program had a proper concurrent relationship with nonradar measures, and the difficulty level was approximately correct. Information from data collected appeared to be asymptoting, and it was recommended that the program could begin pass/fail. The data for this study were collected prior to the air traffic control specialist's strike, and following the strike the Academy radar phase was sequenced out of the basic training curriculum to a later point (after the developmental ATCS had successfully checked out at the field facility in a nonradar position).

This report describes recent developments in the LENS facility, flow field calibration studies, and aerothermal and aero-optical measurements to evaluate the turbulent flow field characteristics of seeker head configurations in hypervelocity airflow. The development of the LENS facility to run at pressure levels up to 30,000 psi and temperatures up to 14,000 deg R are reviewed. Issues associated with diaphragm performance, reservoir configuration, throat melting and burning, and modifications to the facility for large recoil loads at high pressure operation are briefly reviewed. Flow field measurements made during calibration studies are compared with computer predictions. Validation studies with simple seeker head aperture configurations in high enthalpy flows are then discussed. The models and aerothermal and aero-optical instrumentation used in these studies are described. The measurements obtained in flows up to 12,000 ft/sec are compared with similar measurements at lower velocities, simple correlation techniques, and detailed computer simulations.

This poster presentation reviews the process used to validate the GOES-10 satellite derived cloud and radiative properties. The ARM Mobile Facility (AMF) deployment at Pt Reyes, CA as part of the Marine Stratus Radiation Aerosol and Drizzle experiment (MASRAD), 14 March - 14 September 2005 provided an excellent chance to validate satellite cloud-property retrievals with the AMF's flexible suite of ground-based remote sensing instruments. For this comparison, NASA LaRC GOES10 satellite retrievals covering this region and period were re-processed using an updated version of the Visible Infrared Solar-Infrared Split-Window Technique (VISST), which uses data taken at 4 wavelengths (0.65, 3.9,11 and 12 m resolution), and computes broadband fluxes using improved CERES (Clouds and Earth's Radiant Energy System)-GOES-10 narrowband-to-broadband flux conversion coefficients. To validate MASRAD GOES-10 satellite-derived cloud property data, VISST-derived cloud amounts, heights, liquid water paths are compared with similar quantities derived from available ARM ground-based instrumentation and with CERES fluxes from Terra.

When installing a computer system there are many issues which the Information Systems manager must face. This thesis will identify and discuss some of those issues as they pertain to the installation of the Information Sciences Laboratory in Ingersoll Hall, Naval Postgraduate School. The laboratory will contain three local area networks and a number of specialized workstations. The recommendations made in this thesis are the floor plans showing a possible configuration for the laboratory.

It has been hypothesized that continuous ground-based remote sensing measurements from active and passive remote sensors combined with regular soundings of the atmospheric thermodynamic structure can be combined to describe the effects of clouds on the clear sky radiation fluxes. We critically test that hypothesis in this paper and a companion paper (Part II). Using data collected at the Southern Great Plains (SGP) Atmospheric Radiation Measurement (ARM) site sponsored by the U.S. Department of Energy, we explore an analysis methodology that results in the characterization of the physical state of the atmospheric profile at time resolutions of five minutes and vertical resolutions of 90 m. The description includes thermodynamics and water vapor profile information derived by merging radiosonde soundings with ground-based data, and continues through specification of the cloud layer occurrence and microphysical and radiative properties derived from retrieval algorithms and parameterizations. The description of the atmospheric physical state includes a calculation of the infrared and clear and cloudy sky solar flux profiles. Validation of the methodology is provided by comparing the calculated fluxes with top of atmosphere (TOA) and surface flux measurements and by comparing the total column optical depths to independently derived estimates. We find over a 1-year period of comparison in overcast uniform skies, that the calculations are strongly correlated to measurements with biases in the flux quantities at the surface and TOA of less than 10% and median fractional errors ranging from 20% to as low as 2%. In the optical depth comparison for uniform overcast skies during the year 2000 where the optical depth varies over 3 orders of magnitude we find a mean positive bias of 46% with a median bias of less than 10% and a 0.89 correlation coefficient. The slope of the linear regression line for the optical depth comparison is 0.86 with a normal deviation of 20% about this line. In addition to a case study where we examine the cloud radiative effects at the TOA, surface and atmosphere by a middle latitude synoptic-scale cyclone, we examine the cloud top pressure and optical depth retrievals of ISCCP and LBTM over a period of 1 year. Using overcast period from the year 2000, we find that the satellite algorithms tend to bias cloud tops into the middle troposphere and underestimate optical depth in high optical depth events (greater than 100) by as much as a factor of 2.

The Galileo Optical Experiment (GOPEX) has demonstrated the first laser communications uplink to a deep space vehicle. The optical design and validation tests performed at the Table Mountain Facility (TMF) transmitter site are described. The system used a 0.6-m telescope and an optical system at coude focus to produce the uplink beam. The optical system used a pulsed neodymium:yttrium-aluminum-garnet (Nd:Yag) laser and beam diverger optics to produce the required optical output. In order to validate the optical design, a number of uplinks were performed on Earth-orbiting satellites (e.g., Lageos 1 and 2).

Wind tunnel experiments will continue to be a primary source of validation data for many types of mathematical and computational models in the aerospace industry. The increased emphasis on accuracy of data acquired from these facilities requires understanding of the uncertainty of not only the measurement data but also any correction applied to the data. One of the largest and most critical corrections made to these data is due to wall interference. In an effort to understand the accuracy and suitability of these corrections, a statistical validation process for wall interference correction methods has been developed. This process is based on the use of independent cases which, after correction, are expected to produce the same result. Comparison of these independent cases with respect to the uncertainty in the correction process establishes a domain of applicability based on the capability of the method to provide reasonable corrections with respect to customer accuracy requirements. The statistical validation method was applied to the version of the Transonic Wall Interference Correction System (TWICS) recently implemented in the National Transonic Facility at NASA Langley Research Center. The TWICS code generates corrections for solid and slotted wall interference in the model pitch plane based on boundary pressure measurements. Before validation could be performed on this method, it was necessary to calibrate the ventilated wall boundary condition parameters. Discrimination comparisons are used to determine the most representative of three linear boundary condition models which have historically been used to represent longitudinally slotted test section walls. Of the three linear boundary condition models implemented for ventilated walls, the general slotted wall model was the most representative of the data. The TWICS code using the calibrated general slotted wall model was found to be valid to within the process uncertainty for test section Mach numbers less than or equal to 0.60. The scatter among the mean corrected results of the bodies of revolution validation cases was within one count of drag on a typical transport aircraft configuration for Mach numbers at or below 0.80 and two counts of drag for Mach numbers at or below 0.90.

Available from National Technical Information Service, Springfield, Va

The various issues associated with the use of integrated flight management systems in aircraft were discussed. To address these issues a fixed base integrated flight research (IFR) simulation of a helicopter was developed to support experiments that contribute to the understanding of design criteria for rotorcraft cockpits incorporating advanced integrated flight management systems. A validation experiment was conducted that demonstrates the main features of the facility and the capability to conduct crew/system integration research.

The Adaptive Optics Facility (AOF) project envisages transforming one of the VLT units into an adaptive telescope and providing its ESO (European Southern Observatory) second generation instruments with turbulence corrected wavefronts. For MUSE and HAWK-I this correction will be achieved through the GALACSI and GRAAL AO modules working in conjunction with a 1170 actuators Deformable Secondary Mirror (DSM) and the new Laser Guide Star Facility (4LGSF). Multiple wavefront sensors will enable GLAO and LTAO capabilities, whose performance can greatly benefit from a knowledge about the stratification of the turbulence in the atmosphere. This work, totally based on end-to-end simulations, describes the validation tests conducted on a Cn2 profiler adapted for the AOF specifications. Because an absolute profile calibration is strongly dependent on a reliable knowledge of turbulence parameters r0 and L0, the tests presented here refer only to normalized output profiles. Uncertainties in the input parameters inherent to the code are tested as well as the profiler response to different turbulence distributions. It adopts a correction for the unseen turbulence, critical for the GRAAL mode, and highlights the effects of masking out parts of the corrected wavefront on the results. Simulations of data with typical turbulence profiles from Paranal were input to the profiler, showing that it is possible to identify reliably the input features for all the AOF modes.

The NASA White Sands Test Facility (WSTF) has developed an entirely aqueous final cleaning and verification process to replace the current chlorofluorocarbon (CFC) 113 based process. This process has been accepted for final cleaning and cleanliness verification of WSTF ground support equipment. The aqueous process relies on ultrapure water at 50 C (323 K) and ultrasonic agitation for removal of organic compounds and particulate. The cleanliness is verified bv determining the total organic carbon (TOC) content and filtration with particulate counting. The effectiveness of the aqueous methods for detecting hydrocarbon contamination and particulate was compared to the accepted CFC 113 sampling procedures. Testing with known contaminants, such as hydraulic fluid and cutting and lubricating oils, to establish a correlation between aqueous TOC and CFC 113 nonvolatile residue (NVR) was performed. Particulate sampling on cleaned batches of hardware that were randomly separated and sampled by the two methods was performed. This paper presents the approach and results, and discusses the issues in establishing the equivalence of aqueous sampling to CFC 113 sampling, while describing the approach for implementing aqueous techniques on Space Shuttle Propulsion hardware.

The NASA White Sands Test Facility (WSTF) has developed an entirely aqueous final cleaning and verification process to replace the current chlorofluorocarbon (CFC) 113 based process. This process has been accepted for final cleaning and cleanliness verification of WSTF ground support equipment. The aqueous process relies on ultrapure water at 50 C (323 K) and ultrasonic agitation for removal of organic compounds and particulate. The cleanliness is verified bv determining the total organic carbon (TOC) content and filtration with particulate counting. The effectiveness of the aqueous methods for detecting hydrocarbon contamination and particulate was compared to the accepted CFC 113 sampling procedures. Testing with known contaminants, such as hydraulic fluid and cutting and lubricating oils, to establish a correlation between aqueous TOC and CFC 113 nonvolatile residue (NVR) was performed. Particulate sampling on cleaned batches of hardware that were randomly separated and sampled by the two methods was performed. This paper presents the approach and results, and discusses the issues in establishing the equivalence of aqueous sampling to CFC 113 sampling, while describing the approach for implementing aqueous techniques on Space Shuttle Propulsion hardware.

A validation test has recently been constructed for wall interference methods as applied to the National Transonic Facility (NTF). The goal of this study was to begin to address the uncertainty of wall-induced-blockage interference corrections, which will make it possible to address the overall quality of data generated by the facility. The validation test itself is not specific to any particular modeling. For this present effort, the Transonic Wall Interference Correction System (TWICS) as implemented at the NTF is the mathematical model being tested. TWICS uses linear, potential boundary conditions that must first be calibrated. These boundary conditions include three different classical, linear. homogeneous forms that have been historically used to approximate the physical behavior of longitudinally slotted test section walls. Results of the application of the calibrated wall boundary conditions are discussed in the context of the validation test.

The test bed developed at JPL for experimental evaluation of new technologies for the control of large flexible space structures is described. The experiment consists of a flexible spacecraft dynamic simulator, sensors, actuators, a microcomputer, and an advanced programming environment. The test bed has been operational for over a year, and thus far nine experiments were completed or are currently in progress. Several of these experiments were reported at the 1987 CSI conference, and several recent ones are documented in this paper, including high order adaptive control, non-parametric system identification, and mu-synthesis robust control. An aggressive program of experiments is planned for the forseeable future.

No abstract available

In anticipation of increasing stringent environmental regulations. Lawrence Livermore National Laboratory (LLNL) is proposing to modify an existing facility to add a 60-kg firing chamber and related support areas. This modification will provide blast-effects containment for most of its open-air, high-explosive, firing operations. Even though these operations are within the current environment limits, containment of the blast effects and hazardous debris will further drastically reduce emissions to the environment and minimize the hazardous waste generated.

Construction in the AFIT combustion facility is complete and the objective of this report is to explain the steps taken to make the laboratory operational. The infinite radius Ultra-Compact Combustor (UCC) sectional model has been delivered and is fully installed with all fuel, air and instrument lines. Every major system in the lab has been tested and is functioning properly. Laboratory operating procedure has been established to ensure both safety and continuity in experimental results. Finally, the lab has been certified through official safety channels and combustion experiments are underway. The unique capability of the AFIT combustion laboratory is the laser diagnostic system. The laser system has been configured for OH Laser-Induced Fluorescence (LIF) and initial experiments were performed on a premixed, laminar flame produced by a Hencken burner. The LIF methods accurately measured the OH concentration and temperature of the flame as compared to theoretical equilibrium flame data with an overall system uncertainty of approximately 2.5%. Therefore, the laser system has been calibrated and is ready for future use.

All systems and processes require some form of data for operation and decision making. Critical decisions or operations require that a high emphasis be placed on validation of data for its intended use. Data validation techniques have evolved as data acquisition and processing have advanced progressively from analog to digital acquisition and processing. This progression will be examined, and the corresponding efforts toward validation of data will be addressed.

This Validation Summary Report describes the extent to which a specific Ada compiler conforms to the Ada Standard, ANSI/MIL-STD-1815A. This report explains all technical terms used within it and thoroughly reports the results of testing this compiler using the Ada Compiler Validation Capability. An Ada compiler must be implemented according to the Ada Standard, and any implementation-dependent features must conform to the requirements of the Ada Standard. The Ada Standard must be implemented in its entirety, and nothing can be implemented that is not in the Standard. Even though all validated Ada compilers conform to the Ada Standard, it must be understood that some differences do exist between implementations. The Ada Standard permits some implementation dependencies--for example, the maximum length of identifiers or the maximum values of integer types. Other differences between compilers result from the characteristics of particular operating system, hardware, or implementation strategies. All the dependencies observed during the process of testing this compiler are given in this report. The information in this report is derived from the test results produced during validation testing. The validation process includes submitting a suite of standardized tests, the ACVC, as inputs to an Ada compiler and evaluating the results. (kr)

This Validation Summary Report describes the extent to which a specific Ada compiler conforms to the Ada Standard, ANSI/MIL-STD-1815A. This report explains all technical terms used within it and thoroughly reports the results of testing this compiler using the Ada Compiler Validation Capability. An Ada compiler must be implemented according to the Ada Standard, and any implementation-dependent features must conform to the requirements of the Ada Standard. The Ada Standard must be implemented in its entirety, and nothing can be implemented that is not in the Standard. Even though all validated Ada compilers conform to the Ada Standard, it must be understood that some differences do exist between implementations. The Ada Standard permits some implementation dependencies--for example, the maximum length of identifiers or the maximum values of integer types. Other differences between compilers result from the characteristics of particular operating systems, hardware, or implementation strategies. All the dependencies observed during the process of testing this compiler are given in this report. The information in this report is derived from the test results produced during validation testing. The validation process includes submitting a suite of standardized tests, the ACVC, as inputs to an Ada compiler and evaluating the results. (KR)

This article is from BMC International Health and Human Rights , volume 13 . Abstract Background: Governance has been cited as a key determinant of economic growth, social advancement and overall development. Achievement of millennium development goals is partly dependant on governance practices. In 2007, Health Systems 20/20 conducted an Internet-based survey on the practice of good governance. The survey posed a set of good practices related to health governance and asked respondents to indicate whether their experience confirmed or disconfirmed those practices. We applied the 17 governance statements in rural health facilities of Zambia. The aim was to establish whether the statements were reliable and valid for assessing governance practices at primary care level. Methods: Both quantitative and qualitative methods were used. We first applied the governance statements developed by the health system 20/20 and then conducted focus group discussion and In-depth interviews to explore some elements of governance including accountability and community participation. The target respondents were the health facility management team and community members. The sample size include 42 health facilities. Data was analyzed using SPSS version 17 and Nvivo version 9. Results: The 95% one-sided confidence interval for Cronbach’s alpha was between 0.69 and 0.74 for the 16 items.The mean score for most of the items was above 3. Factor analysis yielded five principle components: Transparency, community participation, Intelligence & vision, Accountability and Regulation & oversight. Most of the items (6) clustered around the transparency latent factor. Chongwe district performed poorly in overall mean governance score and across the five domains of governance. The overall scores in Chongwe ranged between 51 and 94% with the mean of 80%. Kafue and Luangwa districts had similar overall mean governance scores (88%). Community participation was generally low. Generally, it was noted that community members lacked capacity to hold health workers accountable for drugs and medical supplies. Conclusions: The study successfully validated and applied the new tool for evaluating health system governance at health facility level. The results have shown that it is feasible to measure governance practices at health facility level and that the adapted tool is fairly reliable with the 95% one-sided confidence interval for Cronbach’s alpha laying between 0.69 and 0.74 for the 16 items. Caution should be taken when interpreting overall scores as they tended to mask domain specific variations.

This article is from Epidemiology and Infection , volume 142 . Abstract Understanding the spatial distribution of disease is critical for effective disease control. Where formal address networks do not exist, tracking spatial patterns of clinical disease is difficult. Geolocation strategies were tested at rural health facilities in western Kenya. Methods included geocoding residence by head of compound, participatory mapping and recording the self-reported nearest landmark. Geocoding was able to locate 72·9% [95% confidence interval (CI) 67·7–77·6] of individuals to within 250 m of the true compound location. The participatory mapping exercise was able to correctly locate 82·0% of compounds (95% CI 78·9–84·8) to a 2 × 2·5 km area with a 500 m buffer. The self-reported nearest landmark was able to locate 78·1% (95% CI 73·8–82·1) of compounds to the correct catchment area. These strategies tested provide options for quickly obtaining spatial information on individuals presenting at health facilities.

This Validation Summary Report describes the extent to which a specific Ada compiler conforms to the Ada Standard, ANSI/MIL-STD-1815A. This report explains all technical terms used within it and thoroughly reports the results of testing this compiler using the Ada Compiler Validation Capability. An Ada compiler must be implemented according to the Ada Standard, and any implementation-dependent features must conform to the requirements of the Ada Standard. The Ada Standard must be implemented in its entirety, and nothing can be implemented that is not in the Standard. Even though all validation Ada compilers conform to the Ada Standard, it must be understood that some differences do exist between implementations. The Ada Standard permits some implementation dependencies--for example, the maximum length of identifiers or the maximum values of integer types. Other differences between compilers result from the characteristics of particular operating systems, hardware, or implementation strategies. All the dependencies observed during the process of testing this compiler are given in this report. The information in this report is derived from the test results produced during validation testing. The validation process includes submitting a suite of standardized tests, the ACVC, as inputs to an Ada compiler and evaluating the results.

The Wright Laboratory's expanding requirement for reliable resident exhaust nozzle testing capability necessitated the verification of the experimental capability of the Trisonic Gasdynamics Facility (TGF) located at Wright-Patterson Air Force Base. A validation test, directed toward the TGF's nozzle testing capability, compared surface pressure data taken from an axisymmetric AGARD reference nozzle from a wind tunnel test performed at the Propulsion Wind Tunnel (PWT) at Arnold Engineering Development Center (AEDC). Boattail pressure distributions and pressure drag measurements were compared between the facilities. Cross-sectional blockage caused significant differences between boattail pressures and pressure drag coefficients between facilities. Computational fluid dynamics (CFD) tools were used to aid understanding of differences found in the comparison study. A series of CFD simulations aimed at determining the actual freestream flow Mach number is recommended to improve flow simulating accuracy in the TGF.... Wind tunnel, Simulation, Drag, Validation, Boattail, Computational Fluid Dynamics(CFD), Pressure coefficient, Blockage

Tests were conducted on a four-finned, ogive-cylinder store model which was mounted on the von Karman Gas Dynamics Facility (VKF) Captive Trajectory System (CTS) in the Arnold Engineering Development Center (AEDC) supersonic Wind Tunnel A. The purpose of these tests was to provide information necessary for an independent check on the VKF CTS trajectory mode results. Grid and trajectory data were obtained for the store, both in the free stream and in the interference flow field of a generalized parent-aircraft model. The Mach number was 1.63, with Reynolds numbers per foot of 5.0 and 3.8 million. Grid data from these tests were used in conjunction with the Air Force Flight Dynamics Laboratory (AFFDL) Six-Degree-of-Freedom Computer Program (SDFCP) to simulate the trajectories obtained by the VKF CTS. These SDFCP simulations compared favorably with the CTS trajectories, providing an important compared favorably with the CTS trajectories, providing an important independent verification of the VKF CTS trajectory mode results. This report documents this validation effort and provides a general description of the VKF CTS as well as guidelines for potential users of this system.

This Validation Summary Report describes the extent to which a specific Ada compiler conforms to the Ada Standard, ANSI/MIL-STD-1815A. This report explains all technical terms used within it and thoroughly reports the results the results of testing this compiler using the Ada Compiler Validation Capability. An Ada compiler must be implemented according to the Ada Standard, and any implementation-dependent features must conform to the requirements of the Ada Standard. The Ada Standard must be implemented in its entirety, and nothing can be implemented that is not in the Standard. Even though all validated Ada compilers conform to the Ada Standard, it must be understood that some differences do exist between implementations. The Ada Standard permits some implementation dependencies--for example, the maximum length of identifiers or the maximum values of integer types. Other differences between compilers result from the characteristics of particular operating systems, hardware, or implementation strategies. All the dependencies observed during the process of testing this compiler are given in this report. The information in this report is derived from the test results produced during validation testing. The validation process includes submitting a suite of standardized tests, ACVC, as inputs to an Ada compiler and evaluating the results. (KR)

This study investigated the design parameters necessary for the construction and use of a testing facility built to test the combustor section of engines. User inputs were acquired by interview and used in the decisions made in arrangement of pieces of machinery and how different systems were to interact. The design was then carried out as the various parts of the facility were built and installed. Software was designed which controlled the different parts of the combustion process and monitored the different products of combustion as well as the properties of the air and fuel used in the combustion. These measurements were analyzed to determine the efficiency of combustion in the combustor. All systems and measurements were conducted and operated while following the guidance set forth in SAE ARP 1256. Safeguard systems were also designed into the facility to maintain a safe work environment for the user. These safeguards include automatic fuel shut-offs, heater shut-offs, and general system power downs. While the system was originally designed to handle the testing of a planar 2-D combustion chamber, the labs now have the capability to analyze any type of system that requires a combustion analyzer that follows SAE ARP 1256, a system that requires heated air or fuel, a system that requires an exhaust system to pull gasses out of the testing area, or a system that needs open flame. These additional capabilities allow further research to be conducted on site with an increase in ability to report different results.

Data are acquired in a simple coannular He/air supersonic jet suitable for validation of CFD (Computational Fluid Dynamics) codes for high speed propulsion. Helium is employed as a non-reacting hydrogen fuel simulant, constituting the core of the coannular flow while the coflow is composed of air. The mixing layer interface between the two flows in the near field and the plume region which develops further downstream constitute the primary regions of interest, similar to those present in all hypersonic air breathing propulsion systems. A computational code has been implemented from the experiment's inception, serving as a tool for model design during the development phase.

Between 1997 and 1999, a Working Group on the feasibility of collaborative, multi-facility windtunnel testing for the validation of Computational Fluid Dynamics Codes (CFD) has established the following results: Windtunnel tests are the main source of CFD validation but all have specific bias errors. Testing of the same model in several facilities can better establish the level of uncertainty in windtunnel tests and hence help assess possible differences between CFD and windtunnel tests. The working group, after an initial inquiry, established the need for CFD validation for fighter aircraft, transport type aircraft, missiles and helicopters. Effort and cost can be controlled efficiently and would permit the improvement of CFD Codes for considerable cost saving in future developments.

This Validation Summary Report describes the extent which a specific Ada compiler conforms to the Ada Standard, ANSI/MIL-STD-1815A. This report explains all technical terms used within it and thoroughly reports the results of testing this compiler using the Ada Compiler Validation Capability. An Ada compiler must be implemented according to the Ada Standard, and any implementation-dependent features must conform to the requirements of the Ada Standard. The Ada Standard must be implemented in its entirety, and nothing can be implemented that is not in the Standard. Even though all validated Ada compilers conform to the Ada Standard, it must be understood that some differences do exist between implementations. The Ada Standard permits some implementation dependencies--for example, the maximum length of indentifiers or the maximum values of integer types. Other differences between compilers result from the characteristics of particular operating systems, hardware, or implementation strategies. All the dependencies observed during the process of testing this compiler are given in this report. The information in this report is derived from the test results produced during validation testing. The validation process includes submitting a suite of standardized tests, the ACVC, as inputs to an Ada compiler and evaluating the results. (kr)

The Harry Diamond Lab. provided high-altitude electromagnetic pulse (HEMP) and partial lightning hardness verification testing to a high-frequency radio facility for the FAA. The facility consisted of a shielded enclosure with antennas and cables connected through protective devices at the shield to dummy loads within the shield. It was exposed to low-level radiation with measurements of internal fields extrapolated to threat levels and compared to specific criteria. Each typical penetration was injected with a simulated lightning source, and internal measurements were compared to specific criteria. Although criteria were not always met, it was judged with confidence that the facility would protect radio equipment. It was noted that the ac power spark gap would remain shorted until ac power shut down, resulting in system upset. Keywords: Electromagnetic shielding; Shield enclosure; HEMP test; Lightning test; HF radio.

Arnold Engineering Development Center (AEDC) recently acquired the Facility Aerodynamics Validation and Operations Research (FAVOR) model for use as a standard check model for Propulsion Wind Tunnel (PWT) 16T. The test article is a 5% scale model of the F-111 with new wings having a NACA 64-210 profile, a fixed sweep angle of 35 deg, and a span of 48 in. The plan is to periodically install the model and test across the facility capabilities to validate that tunnel operational characteristics have not changed. The first test of this model was recently completed as the baseline for future tests. While the internal balance and installed pressure taps were the primary source of data acquired, several other types of on- and off-body data were acquired. These included pressure-sensitive paint (PSP), background oriented schlieren (BOS), laser vapor screen, and planar doppler velocimetry (PDV). Pressure-sensitive paint data were acquired for demonstration of the techniques' capability to measure surface pressure and determine total vehicle loads and for use in computational fluid dynamics (CFD) validation. The PSP data were compared to and validated by conventional pressure data measured on the model and with total vehicle loads measured by the internal balance. This report documents the results from the PSP and presents the data comparisons.

This paper discusses the design and initial validation of a newly constructed aeroacoustic anechoic test facility at the University of Florida. The facility will enable and assist research in the areas of aeroacoustics, structural acoustics, and industrial noise/vibration control. General facility features and characteristics are described and documented. Experimental results focus on the free-field characteristics of the chamber via the ISO 3745 standard and preliminary evaluations of the acoustic data quality for subsonic axisymmetric turbulent jet noise measurements. Initial free-field results comply with the tolerances set by the ISO standard except for a few bands close to the corner containing the chamber door. The preliminary jet noise measurements yield reasonable comparisons to the fine-scale turbulent jet noise similarity spectrum at 90 degrees. The results also reveal the need for acoustic treatment and vibration control of the chamber traverse and fan that supplies supplemental entrainment air.

This report summarizes the effort to generate a library of quantitative infrared spectra of chemical warfare agents and related materials and biosimulants. The results of tests to validate the equipment and procedures to be used in the laboratory are discussed.

The U.S. Army Crew Station Research and Development Branch (CSRDB) of the Aircraft Simulation Division (AVSCOM) was tasked by the Light Helicopter Program Manager (LH-PM) to provide training to Army personnel in advanced aircraft simulation technology. The purpose of this training was to prepare different groups of pilots to support and evaluate two contractor simulation efforts during the Demonstration/Validation (DEM/VAL) phase of the LH program. The personnel in the CSRDB developed mission oriented training programs to accomplish the objectives, conduct the programs, and provide guidance to army personnel and support personnel throughout the DEM/VAL phase.

The AFIT small-scale combustion facility is complete and its first experiment designed and built. Beginning with the partially built facility, detailed designs have been developed to complete the laboratory in order to run small-scale combustion experiments at atmospheric pressure. A sectional model of the Ultra-Compact Combustor has also been designed and built. Although the lab's specific design intent was to study the UCC's cavity-vane interaction, facility flexibility has also been maintained for future work. The design enabled the completion of liquid fuel and air delivery systems, power and control systems, and test equipment. The design includes failsafe operation, remote control, and adherence to SAE ARP 1256 testing standards. Construction of the laboratory has forced design changes as new obstacles arose. As system construction has been completed validation and troubleshooting have been undertaken. The AFIT facility can now deliver air in two separately controlled air lines at up to 530 K (500 deg F), at delivery rates of 0.12 kg/s (200 SCFM) for the main line and 0.03 kg/s (60 SCFM) for the secondary. A continuous dual syringe pump can deliver liquid fuel at up to 5.67 mL/s for JP-8 equivalence ratios up to 4. Safe, remote ignition and shutdown are in place and all test equipment fundamental to combustion is installed. The addition of an advanced laser combustion diagnostics system adds more unique capability to the laboratory. The laser system will provide instantaneous Raman and Raman spectroscopy, Coherent Anti-Stokes Raman Scattering, Planar Laser-Induced Fluorescence, Laser-Induced Incandescence and Planar Imaging Velocimetry diagnostic techniques.

A unique assessment of acoustic similarity scaling laws and acoustic analogy methodologies in predicting the far-field acoustic signature from a sub-scale altitude rocket test facility at the NASA Stennis Space Center was performed. A directional, point-source similarity analysis was implemented for predicting the acoustic far-field. In this approach, experimental acoustic data obtained from "similar" rocket engine tests were appropriately scaled using key geometric and dynamic parameters. The accuracy of this engineering-level method is discussed by comparing the predictions with acoustic far-field measurements obtained. In addition, a CFD solver was coupled with a Lilley's acoustic analogy formulation to determine the improvement of using a physics-based methodology over an experimental correlation approach. In the current work, steady-state Reynolds-averaged Navier-Stokes calculations were used to model the internal flow of the rocket engine and altitude diffuser. These internal flow simulations provided the necessary realistic input conditions for external plume simulations. The CFD plume simulations were then used to provide the spatial turbulent noise source distributions in the acoustic analogy calculations. Preliminary findings of these studies will be discussed.

This Validation Summary Report describes the extent to which a specific Ada compiler conforms to the Ada Standard, ANSI/MIL-STD-1815A. This report explains all technical terms used within it and thoroughly reports the results of testing this compiler using the Ada Compiler Validation Capability. An Ada compiler must be implemented according to the Ada Standard, and any implementation-dependent features must conform to the requirements of the Ada Standard. The Ada Standard must be implemented in its entirety, and nothing can be implemented that is not in the Standard. Even though all validation Ada compilers conform to the Ada Standard, it must be understood that some differences do exist between implementations. The Ada Standard permits some implementation dependencies--for example, the maximum length of identifiers or the maximum values of integer types. Other differences between compilers result from the characteristics of particular operating systems, hardware, or implementation strategies. All the dependencies observed during the process of testing this compiler are given in this report. The information in this report is derived from the test results produced during validation testing. The validation process includes submitting a suite of standardized tests, the ACVC, as inputs to an Ada compiler and evaluating the results.

This Validation Summary Report describes the extent to which a specific Ada compiler conforms to the Ada Standard, ANSI/MIL-STD-1815A. This report explains all technical terms used within it and thoroughly reports the results of testing this compiler using the Ada Compiler Validation Capability. An Ada compiler must be implemented according to the Ada Standard, and any implementation-dependent features must conform to the requirements of the Ada Standard. The Ada Standard must be implemented in its entirety, and nothing can be implemented that is not in the Standard. Even though all validation Ada compilers conform to the Ada Standard, it must be understood that some differences do exist between implementations. The Ada Standard permits some implementation dependencies--for example, the maximum length of identifiers or the maximum values of integer types. Other differences between compilers result from the characteristics of particular operating systems, hardware, or implementation strategies. All the dependencies observed during the process of testing this compiler are given in this report. The information in this report is derived from the test results produced during validation testing. The validation process includes submitting a suite of standardized tests, the ACVC, as inputs to an Ada compiler and evaluating the results.

When installing a computer system there are many issues which the Information Systems manager must face. This thesis will identify and discuss some of those issues as they pertain to the installation of the Information Sciences Laboratory in Ingersoll Hall, Naval Postgraduate School. The laboratory will contain three local area networks and a number of specialized workstations. The recommendations made in this thesis are the floor plans showing a possible configuration for the laboratory. Keywords: Local area networks; Computer room installation; Thesis.

The Army Environmental Center (AEC) Base Realignment and Closure (BRAC) Division tasked Home Engineering Services, The. to perform data validation in support of ongoing Remedial Investigations/Feasibility Studies (RI(FS) at the Woodbridge Research Facility (WRF), Virginia. This plan presents how Home Engineering will perform data validation for WRF site. The project objective is to validate 100% of the WRF environmental analytical data to ensure that the data quality objectives described in the Quality Assurance (QA) Plan are met and that no Systematic errors exist within the data sets. All field blanks, trip blanks, and equipment rinse blanks will be checked by ICF Kaiser in accordance with Section 4.4 of WRF QA Plan. The validation effort will verify that the WRF environmental data (1) are of known quality, (2) are technically valid, (3) satisfy the project objectives, and (4) are useable for their intended purpose. The data validation process will perform the following: (a) Verify that no systematic errors exist within the data sets (b) Assess field quality control (QC) samples to determine if sampling has adversely impacted the reported results (c) Tabulate QC outliers used to assess both method and laboratory performance and determine the impact on the reported results (d) Provide measures of data quality in terms of precision, accuracy, and completeness 1.2 Site Information Woodbridge Research Facility - The types of samples collected at WRF site include sediment/soil, water, and tissues. Sediment/soil samples were analyzed for: Metals, Pesticide/Polychlorinated biphenyls (P/PCBs), Dioxins, Volatile Organic Carbons (VOCs), Semivolatile Organic Carbons (SVOCs), and Polychlorinated Terphenyls (PCT). Water samples were analyzed for Metals, VOCs, SVOCs, P/PCBs, and PCTs. Tissues were analyzed for Metals, P/PCBs, PCTs, and PAlls.

The Solar Cell Calibration Facility (SCCF) experiment was designed and built to evaluate the effect of the Earth's upper atmosphere on the calibration of solar cell standards. During execution of the experiment, a collection of carefully selected solar cells was flown on the shuttle, and reflown on a high-altitude balloon, then their outputs were compared. After correction to standard temperature and intensity values of 28 C and an Earth-Sun distance of 1 AU, the solar cell outputs during the two flights were found to be identical. The conclusion is therefore that the high-altitude balloon flights are very good vehicles for calibrating solar cells for use as space flight reference standards.