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Ultra-Efficient Engine Technology (UEET) Proof of Concept Compressor, Advanced Compressor Casing Treatment testing, First Research Configuration (concentric grooves)

Ultra-Efficient Engine Technology (UEET), Proof of Concept Compressor, Advanced Compressor Casing Treatment testing; close up - throttle valve -wide open

This volume was digitized and made accessible online due to deterioration of the original print copy.

The goal of this study is to create and test a biogas petrol mixture that can power spark ignition engines. A biogas petrol blend with a 20 80 ratio was created as a substitute fuel for spark ignition engines. To evaluate the performance of the fuels, comparison tests using gasoline and a biogas petrol combination were conducted on the test bed. The experiments findings demonstrated that the biogas petroleum blend produced higher torque, brake power, indicated power, brake thermal efficiency, and brake mean effective pressure yet used less fuel and heated the exhaust less than gasoline. According to the studys findings, a biogas petrol mix spark ignition engine was shown to be cheap, use less fuel, and contribute to sanitation and fertiliser production. Prof. Mihir Kumar Pandey | Anil Kumar Dwivedi "Biogas-Petrol Blend Development and Testing as Alternative Fuel for Spark Ignition Engine" Published in International Journal of Trend in Scientific Research and Development (ijtsrd), ISSN: 2456-6470, Volume-7 | Issue-1 , February 2023, URL: https://www.ijtsrd.com/papers/ijtsrd52718.pdf Paper URL: https://www.ijtsrd.com/engineering/mechanical-engineering/52718/biogaspetrol-blend-development-and-testing-as-alternative-fuel-for-spark-ignition-engine/prof-mihir-kumar-pandey

Jet engine being set up for testing with technicians from Propulsion System lab PSL

Ultra-Efficient Engine Technology (UEET) Proof of Concept Compressor, Advanced Compressor Casing Treatment testing, First Research Configuration (concentric grooves)

BY ORDER OF THE EXECUTIVE DIRECTOR Office of the Federal Register Washington, D.C. By Authority of the Code of Federal Regulations: 40 CFR 86.1330-90(b)(5) Name of Legally Binding Document: SAE J1937: Recommended Practice for Engine Testing with Low Temperature Charge Air Cooler Systems in a Dynamometer Test Cell Name of Standards Organization: Society of Automotive Engineers LEGALLY BINDING DOCUMENT This document has been duly INCORPORATED BY REFERENCE into federal regulations and shall be considered legally binding upon all citizens and residents of the United States of America. HEED THIS NOTICE! Criminal penalties may apply for noncompliance. Have a nice day.

BY ORDER OF THE EXECUTIVE DIRECTOR Office of the Federal Register Washington, D.C. By Authority of the Code of Federal Regulations: 40 CFR 86.1330-90(b)(5) Name of Legally Binding Document: SAE J1937: Recommended Practice for Engine Testing with Low Temperature Charge Air Cooler Systems in a Dynamometer Test Cell Name of Standards Organization: Society of Automotive Engineers LEGALLY BINDING DOCUMENT This document has been duly INCORPORATED BY REFERENCE into federal regulations and shall be considered legally binding upon all citizens and residents of the United States of America. HEED THIS NOTICE! Criminal penalties may apply for noncompliance. Have a nice day.

The objectives with the testing, test set-ups, component designs, and the results of the testing of the solar Stirling engine in a parabolic dish system are presented. The most important tests are characterization of receivers, full day performance of complete system, cavity and aperture window test including influence from windeffects, control system tests, radiator system tests and special temperature measurements with infrared camera. The influence on performance of flux distribution depnding on concentrator alignment, and the optimum receiver operating criteria when balancing flux and temperatures on cooled receiver surface while avoiding flux on uncooled surfaces are also discussed.

Thesis advisor, David W. Netzer

Ultra-Efficient Engine Technology (UEET) Proof of Concept Compressor, Advanced Compressor Casing Treatment testing, First Research Configuration (concentric grooves)

Ultra-Efficient Engine Technology (UEET) Proof of Concept Compressor, Advanced Compressor Casing Treatment testing, First Research Configuration (concentric grooves)

Ultra-Efficient Engine Technology (UEET) Proof of Concept Compressor, Advanced Compressor Casing Treatment testing, First Research Configuration (concentric grooves)

Jet engine being set up for testing with technicians from Propulsion System Laboratory (PSL). Image modified to include photographer taking the photo.

A Semi Cryogenic Engine is being developed to power the booster stages of India’s future launch vehicles. Achieving the highest possible specific impulse for a particular propellant combination has always been a key factor for space launch systems. Many of the current rocket engines work on toxic propellants combination like Monomethyl hydrazine (MMH), Nitrogen Tetroxide (N2 O4 ), Unsymmetric Dimethly Hydrazine (UDMH) are difficult to handle. Any failure using this propellant have catastrophic implications on environment. There is an increased thrust to explore environment friendly propellants. Need for high thrust booster for increased payload requirement along with reliability and reusability have provided a new focus that is centered on using high density impulse (LOX/ISR) propellant combination working with oxidizer rich staged combustion (ORSC) cycle. Various developmental activities have been taken up to gain expertise in design of thrust chamber injector, a critical component that largely determines the engine performance and main chamber life. The goals of the effort described here are to establish an empirical knowledge base to provide a fundamental understanding of main chamber injectors and for verification of an injector design methodology for the ORSC cycle. This paper provides a summary of the status of injector developmental activities at LPSC, ISRO. The baseline Preburner and injector operating conditions and geometries are described. Injector performances in tests carried out are briefly discussed.

Testing and analysis of a shrouded turbojet engine with possible application for high speed propulsion on low cost Unmanned Combat Aerial Vehicles (UCAV), Unmanned Aerial Vehicles (UAV) and missiles. The possibility of a turbojet providing thrust at subsonic conditions and the ramjet section providing the thrust in the supersonic regime exists. The combined cycle engine (CCE) could be incorporated into a variety of applications. The building of a new freejet facility and engine test rig at the Naval Postgraduate School enabled dynamic testing of the ongoing development of a turboramjet. The freejet facility and new engine stand performed without exception. The shrouded engine was dynamically tested in a freejet up to Mach 0.4. The engine performance measurements closely matched those predicted by a cycle analysis program, GASTURB. Computational fluid dynamics (CFD) was used to analyze the supersonic inlet at a design point of Mach 2. The results provided by the CFD code, OVERFLOW, matched theoretical flow parameters. The intake design was slightly modified to enhance performance of shock waves in the supersonic flight regime

Jet engine being set up for testing

Ultra-Efficient Engine Technology (UEET), Proof of Concept Compressor, Advanced Compressor Casing Treatment testing; bearing housing and shaft during build-up

Ultra-Efficient Engine Technology (UEET), Proof of Concept Compressor, Advanced Compressor Casing Treatment testing; bearing housing and shaft during build-up

Jet engine being set up for testing

INCONEL 718 panels after impact testing in the Ballistics Impact Lab with Titanium Simulated Jet Engine Blade

Footage of a camouflaged Ferrari LaFerrari and an unexpected engine note. Ferrari is allegedly testing the 2014 1.6L V6 turbo F1 engine using a LaFerrari, as it did in 2005 when it fitted a camouflaged Enzo with a test unit of the V8 engine. ~~~ Ferrari S.p.A. is an Italian sports car manufacturer based in Maranello, Italy. Founded by Enzo Ferrari in 1929, as Scuderia Ferrari, the company sponsored drivers and manufactured race cars before moving into production of street-legal vehicles as Ferrari S.p.A. in 1947. Fiat S.p.A. acquired 50% of Ferrari in 1969 and expanded its stake to 85% in 2008, which it still holds today.[3] Throughout its history, the company has been noted for its continued participation in racing, especially in Formula One, where it has had great success. Ferrari road cars are generally seen as a symbol of speed, luxury and wealth. ~~~ This video has been edited. Credits go to the original uploader.

Twelve firings of the Rocketdyne J-2 rocket engine (S/N 2047) were conducted in Test Cell J-4 of the Large Rocket Facility on March 27 and April 2 and 10, 1968. These firings were accomplished during test periods J4-1801-34, J4-1801-35, and J4-1801-36 at pressure altitudes of approximately 100,000 ft at engine start to investigate S-IVB (1) first burn firings, (2) 6-hr orbital coast restart simulation firings, (3) 80-min orbital coast restart simulation firings, and (4) a partial transition firing to evaluate thrust chamber conditioning temperature effects on engine start transients. Engine operation was satisfactorily accomplished for all firings. One abort resulted when a leak developed in the diaphragm of the engine pneumatic regulator. The accumulated firing duration for the three test periods was 205 sec. The total firing duration of this engine at AEDC through test period J4-1801-36 is 1141 sec resulting from 91 engine firings.

Twenty-four firings and two fuel lead tests of the Rocketdyne J-2 rocket engine were conducted. This testing was in support of the J-2 engine application to the S-II stage of the Saturn V vehicle. The firings were accomplished at pressure altitudes ranging from 55,000 to 116,000 ft at engine start. The primary objective of these firings was to investigate fuel pump operation under conditions of lower than minimum engine model specification fuel pump net positive suction head and maximum thrust chamber fuel flow resistance utilizing an S-II stage center engine configuration fuel low pressure duct designed to simulate the fluid dynamic characteristics experienced during flight. Engine components were thermally conditioned to temperatures as expected during flight. Engine operation appeared to be satisfactory. The total accumulated firing duration for the six test periods was 190 sec. The total firing duration of this engine at AEDC through test period J4-1801-33 is 940 sec, resulting from 79 engine firings.

Twenty-four firings and two fuel lead tests of the Rocketdyne J-2 rocket engine were conducted. This testing was in support of the J-2 engine application to the S-II stage of the Saturn V vehicle. The firings were accomplished at pressure altitudes ranging from 55,000 to 116,000 ft at engine start. The primary objective of these firings was to investigate fuel pump operation under conditions of lower than minimum engine model specification fuel pump net positive suction head and maximum thrust chamber fuel flow resistance utilizing an S-II stage center engine configuration fuel low pressure duct designed to simulate the fluid dynamic characteristics experienced during flight. Engine components were thermally conditioned to temperatures as expected during flight. Engine operation appeared to be satisfactory. The total accumulated firing duration for the six test periods was 190 sec. The total firing duration of this engine at AEDC through test period J4-1801-33 is 940 sec, resulting from 79 engine firings.

A study was conducted of a new testing technique using flow shaping that together with some modifications of the AEDC 16-ft Transonic Propulsion Wind Tunnel will provide the capability to test full-scale inlet/engine configurations with forebody effects at high maneuvering angles at transonic velocities. The method used to obtain the flow simulation for high maneuvering angles utilized auxiliary flow shaping and geometric pitch. An analytical potential flow method was used to determine the configuration of devices necessary to produce the required flow fields; these devices were then checked experimentally to verify the results.

Four firings of the rocketdyne J-2 rocket engine were conducted in Test Cell J-4 of the Large Rocket Facility. These firings were accomplished during test period J4-1801-07 at pressure altitudes ranging from 89,000 to 106, 000 ft at engine start. The objectives of the test included the evaluation of the effect of start tank energy on the oxidizer pump spin speed and the effect of thrust chamber temperature on the fuel pump high level stall margin. Firing 07A was conducted with 12 experimental oxidizer pump primary seal drain tubes attached to the engine. The accumulated firing duration for this test period was 66.5 sec.

It is recommended that the testing completed with Engine 828 be accepted as evidence that the F107-WR-400 engine meets or exceeds the requirements for environmental vibration exposure and mission simulation testing as set forth in the PID Specification, 24235WR-9501A, and the Qualification Test Plan, CMEP 91-4043G, Report No. 78-145-8.

NASA Stennis Space Center engineers conducted a successful cold-flow test of an RS-84 engine component Sept. 24. The RS-84 is a reusable engine fueled by rocket propellant - a special blend of kerosene - designed to power future flight vehicles. Liquid oxygen was blown through the RS-84 subscale preburner to characterize the test facility's performance and the hardware's resistance. Engineers are now moving into the next phase, hot-fire testing, which is expected to continue into February 2004. The RS-84 engine prototype, developed by the Rocketdyne Propulsion and Power division of The Boeing Co. of Canoga Park, Calif., is one of two competing Rocket Engine Prototype technologies - a key element of NASA's Next Generation Launch Technology program.

The variation in emissions over the exhaust area of a General Electric CF6-50 model engine was investigated in order to determine the requirements for a representative sample. The emission measurements were made in a systematic pattern of 120 sample points using a traversing probe system. These data were used to develop detailed emission profiles at three power levels. At idle power, variations over the exhaust area are attributed to the particular fueling pattern used in current CF6-50 model engines. At higher power levels, where uniform fueling is employed, emission levels are more uniform and are characterized by a slightly peaked radial profile. Average values from the 120-point traverse were comapred with selected 12-point averages in the EPA prescribed cruciform pattern. Generally good agreement between the two averages was obtained. (Author)

It is recommended that the testing completed with Engine 828 be accepted as evidence that the F107-WR-400 engine meets or exceeds the requirements for environmental vibration exposure and mission simulation testing as set forth in the PID Specification, 24235WR-9501A, and the Qualification Test Plan, CMEP 91-4043G, Report No. 78-145-8.

The Conference Proceedings contains 19 papers presented at the Propulsion and Energetics 63rd (B) Specialists' Meeting on Engine Cyclic Durability by Analysis and Testing, which was held in Lisse, Netherlands, on 30 May-1 June 1984. The Technical Evaluation Report is included at the beginning of the Proceedings. Questions and answers of the discussions follow each paper. The Specialists' Meeting was arranged in four sessions: Engine Utilization and Accelerated Missions Testing Development (3); Critical Material Characterization (4); Life Assessment Methodologies (4); and Component and Engine Cyclic Testing (8). The Specialists' Meeting surveyed the current state-of-the-art in technological areas related to improving engine life. It considered the technical and economical problems of advanced cyclic testing in the development of engines. Discussed were: relationships between engine utilization and failure modes, accelerated mission testing development, critical material characteristics, component life assessment methods, recent results of component and engine cyclic testing, and future requirements.

An investigation was conducted to determine the feasibility of a low- cost, caseless, solid-fuel integral-rocket ramjet (IRSFRJ) that has no ejecta. Analytical design of a ramjet powered air-to-ground missile capable of being fired from a remotely piloted vehicle or helicopter was accomplished using current JANNAF and Air Force computer codes. The results showed that an IRSFRJ powered missile can exceed the velocity and range of current systems by more than a two to one ratio, without an increase in missile length and weight. A caseless IRSFRJ with a non ejecting port cover was designed and tested. The experimental results of the static tests showed that a low-cost, caseless IRSFRJ with a non-ejectable port cover is a viable design. Rocket ramjet transition was demonstrated and ramjet ignition was found to be insensitive to the booster tail off to air injection timing sequence.

This document reports an experimental study of the effectiveness of dry chemical in extinguishing and delaying reignition of fires resulting from hydrocarbon fuel leaking onto heated surfaces such as can occur in jet engine nacelles. The commercial fire extinguishant dry chemicals tried were, for example, sodium and potassium bicarbonate, carbonate, chloride, and carbamate (Monnex) but we have also tested other metal-halogen and metal-hydroxycarbonate compounds prepared in our own laboratories. Given in this report are: synthetic and preparative procedures for new materials developed; a new concept of fire-control by dry chemical agents; descriptions of experimental assemblages to test dry chemical fire extinguishant efficiencies in controlling fuel fires initiated by hot surfaces; comparative testing data for more than 25 chemical systems in a static assemblage with no airflow across the heated surface, and similar comparative data for more than 10 compounds in a dynamic system with airflows up to 350 ft/sec; and recommendations for future work with one system that fulfills all requirements delineated by the sponsoring agency, and which has been tested in both the Static and Dynamic assemblages with both methodologies confirming it as the most effective system by comparison with the other materials tested.

Five idle-mode firings of the Rocketdyne J-2S rocket engine (S/N J- 112-1A) were conducted in Test Cell J-4 of the Large Rocket Facility on April 17 and 24, 1969. These firings were accomplished at pressure altitudes of approximately 100,000 ft at engine start. The objectives were: (1) to investigate engine idle-mode operating characteristics with a redesigned injector (oxidizer idle-mode compartment consisted of the injector posts in the tenth row from the center of the injector); (2) to determine fuel injection density for varying pump inlet pressures; and (3) to determine engine idle-mode performance. The lowest injection density was 0.055 lbm/cu. ft. with the thrust chamber bypass valve closed. Engine average characteristic velocity for this injector configuration was about 2.6 percent greater than that recorded during tests with the previous injector.

Caterpillar Testing and Adjustment for 3304 Vehicular Engine. Manufactured by Caterpillar in October 1981. Form Number SENR7591-01; Dimensions are: 8 1/2" width by 11" height and weight 307.0 grams; 134 pages. No copyright notice evident and no registration or renewal on file, Public Domain as per Rule 5 of the United States Copyright Statutes. Etext created by Gerard Arthus. http://OpenEducation.org Go to the above site to find out more about the digitization of this item and the on-going attempt to help make 'Knowledge' and 'Information' available to everyone, anywhere, at any time, for no cost. There are many forces at work which are attempting to turn 'Public Domain' information into a commodity which some can milk for a profit. This parasitic use of information which should be freely available for all to access is an Intellectual Crime and should not be tolerated. Hi-resolution images included.

Introduction In Asia, two-wheeled agricultural tractors predominantly use single-cylinder two-stroke diesel engines, which are characterized by high fuel consumption and substantial air pollution. At the same time, the severe environmental impacts of energy production from diminishing fossil fuel reserves are increasingly evident. Therefore, it is essential to develop sustainable and clean energy sources to meet these needs. Biodiesel is an alternative fuel that can be blended with conventional diesel to help reduce environmental pollution. In this study, diesel-biodiesel blends produced from rapeseed, soybean, and palm oil were evaluated for their effects on engine performance metrics, including power (P), torque (T), and specific fuel consumption (SFC). Furthermore, the emissions of pollutants (NOx, HC, CO, and CO₂) from these fuels were measured and modeled using linear and non-linear regression, as well as the adaptive neuro-fuzzy inference system (ANFIS). Materials and Methods To leverage the benefits of palm oil biodiesel, known for its high calorific value, along with the low kinematic viscosity of biodiesel derived from soybean and rapeseed oils, pure diesel was blended with 10% and 20% mixtures of rapeseed, soybean, and palm biodiesel, as well as 10% and 20% combinations of all three biodiesels. These nine fuel blends were tested at four engine speeds (1800, 2100, 2400, and 2700 rpm) under full load conditions. The diesel-biodiesel blends were produced at Sari Agricultural Sciences and Natural Resources University (SANRU) and transported to the engine laboratory at Tarbiat Modares University in Tehran, Iran, for detailed analysis. A total of 36 treatments were evaluated using a randomized complete block design (RCBD), incorporating four engine speeds and nine fuel types. The measured outputs included engine power, torque, specific fuel consumption, and pollutant emissions such as NOx, HC, CO, and CO₂. The collected data were used as input for modeling through both linear and non-linear regression in SPSS software, as well as ANFIS in MATLAB software. Results and Discussion This study evaluated nine diesel-biodiesel blends derived from palm, rapeseed, and soybean oils using a diesel engine in a controlled laboratory setting. Tests were carried out at four engine speeds—1800, 2100, 2400, and 2700 rpm—under full load conditions to assess engine performance and exhaust emissions. The results showed that for all tested fuel blends, power, specific fuel consumption, and pollutant emissions increased with engine speed, while torque decreased. Based on the findings, a blend containing 20% palm biodiesel can be used as an alternative fuel in diesel engines without requiring any modifications. The modeling results indicated that non-linear regression provided better accuracy than linear regression. However, ANFIS demonstrated a much higher correlation between actual and predicted values, with R² exceeding 0.98 for both performance parameters and emissions, compared to R² values below 0.47 for linear regression and below 0.92 for non-linear regression. The ANFIS model achieved its highest and lowest R² values at 0.99 for specific fuel consumption (SFC) and 0.98 for power (P), respectively; substantially higher than those from linear regression, which yielded 0.47 for torque (T) and 0.00 for power. Non-linear regression resulted in R² values of 0.92 for SFC and 0.60 for carbon monoxide (CO), still lower than those achieved by ANFIS. Overall, the highest R² value recorded was 0.7525 for torque, and the lowest was 0.6112 for power. Conclusion Single-cylinder diesel engines, which have high fuel consumption and contribute to air pollution, are commonly used in two-wheel agricultural tractors across Asia. One approach to reducing the environmental impact of fossil fuels is to use biodiesel in these engines without requiring any modifications. The results of this study showed that a 20% blend of palm biodiesel can be an effective alternative fuel for diesel engines, with no need for engine modification. Furthermore, the modeling results indicated a significantly higher correlation (R² > 0.98) between actual and predicted values of performance variables and emissions using ANFIS, compared to linear regression (R² < 0.47) and non-linear regression (R² < 0.92). Therefore, ANFIS can be effectively used to accurately predict engine performance and emission parameters.

INCONEL 718 panels after impact testing in the Ballistics Impact Lab with Titanium Simulated Jet Engine Blade

Thesis (MS)--University. of Minnesota, 1955

No Abstract Available

A screening program to determine the effects of high pressure hydrogen on selected candidate materials for advanced single crystal turbine blade applications is examined. The alloys chosen for the investigation are CM SX-2, CM SX-4C, Rene N-4, and PWA1480. Testing is carried out in hydrogen and helium at 34 MPa and room temperature, with both notched and unnotched single crystal specimens. Results show a significant variation in susceptibility to Hydrogen Environment Embrittlement (HEE) among the four alloys and a marked difference in fracture topography between hydrogen and helium environment specimens.

Learn how the Frisco Fire Department makes sure it’s engines' pumping systems are working properly in this #FriscoFireFacts.

Ultra-Efficient Engine Technology (UEET), Proof of Concept Compressor, Advanced Compressor Casing Treatment testing; close up - throttle valve - partially closed

The NEXT propulsion system is an advanced ion propulsion system presently under development that is oriented towards robotic exploration of the solar system using solar electric power. The subsystem includes an ion engine, power processing unit, feed system components, and thruster gimbal. The Prototype Model engine PM1 was subjected to qualification-level environmental testing in 2006 to demonstrate compatibility with environments representative of anticipated mission requirements. Although the testing was largely successful, several issues were identified including the fragmentation of potting cement on the discharge and neutralizer cathode heater terminations during vibration which led to abbreviated thermal testing, and generation of particulate contamination from manufacturing processes and engine materials. The engine was reworked to address most of these findings, renamed PM1R, and the environmental test sequence was repeated. Thruster functional testing was performed before and after the vibration and thermal-vacuum tests. Random vibration testing, conducted with the thruster mated to the breadboard gimbal, was executed at 10.0 Grms for 2 min in each of three axes. Thermal-vacuum testing included three thermal cycles from 120 to 215 C with hot engine re-starts. Thruster performance was nominal throughout the test program, with minor variations in a few engine operating parameters likely caused by facility effects. There were no significant changes in engine performance as characterized by engine operating parameters, ion optics performance measurements, and beam current density measurements, indicating no significant changes to the hardware as a result of the environmental testing. The NEXT PM1R engine and the breadboard gimbal were found to be well-designed against environmental requirements based on the results reported herein. The redesigned cathode heater terminations successfully survived the vibration environments. Based on the results of this test program and confidence in the engineering solutions available for the remaining findings of the first test program, specifically the particulate contamination, the hardware environmental qualification program can proceed with confidence

The current Space Shuttle Orbital Maneuvering Engine (OME) is pressure fed, utilizing storable propellants. Performance uprating of this engine, through the use of a gas generator driven turbopump to increase operating pressure, is being pursued by the NASA Johnson Space Center (JSC). Component level design, fabrication, and test activities for this engine system have been on-going since 1984. More recently, a complete engine designated the Integrated Component Test Bed (ICTB), was tested at sea level conditions by Aerojet. A description of the test hardware and results of the sea level test program are presented. These results, which include the test condition operating envelope and projected performance at altitude conditions, confirm the capability of the selected Uprated OME (UOME) configuration to meet or exceed performance and operational requirements. Engine flexibility, demonstrated through testing at two different operational mixture ratios, along with a summary of projected Space Shuttle performance enhancements using the UOME, are discussed. Planned future activities, including ICTB tests at simulated altitude conditions, and recommendations for further engine development, are also discussed.

NASA Marshall Space Flight Center (MSFC) has been advancing dynamic optical measurement systems, primarily Digital Image Correlation, for extreme environment rocket engine test applications. The Digital Image Correlation (DIC) technology is used to track local and full field deformations, displacement vectors and local and global strain measurements. This technology has been evaluated at MSFC through lab testing to full scale hotfire engine testing of the J-2X Upper Stage engine at Stennis Space Center. It has been shown to provide reliable measurement data and has replaced many traditional measurement techniques for NASA applications. NASA and AMRDEC have recently signed agreements for NASA to train and transition the technology to applications for missile and helicopter testing. This presentation will provide an overview and progression of the technology, various testing applications at NASA MSFC, overview of Army-NASA test collaborations and application lessons learned about Digital Image Correlation.

Approved For Release 2008/05/29: CIA-RDP80-0081 OA007400450002-2 CENTRAL INTELLIGENCE AGENCY This material contains information affecting the National Defense of the United States within the meaning of the llspionage Laws. Title 18, U.B.C. Secs. 793 and 794, the transmission or revelation of which in any mapper to an uaauthorlaed person in prohibited by law. USSR (Lattrian .W) SUBJECT 1. Raval Activity at Riga 2. Jet Ingine Testing DATE OF INFO. PLACE ACQUIRED DATE ACQUIRED DATE DISTR. NO. OF PAGES REQUIREMENT NO. RD REFERENCES This is UNEVALUATED Information 1. While ship was waitiOg for a pilot off Riga as 12 *7 19gg bete 0330 and 1100, six aubasrines and 20 aril surface warships easrged tray the barb=. *ch of the snrfaae vessels was about 65 fast long and had ane gum an the foredeck and a canvas comet, ayliairiaal ob,ject an the gtiarterde k 2. Of these 20 Vessels, 19 of these pros e4st north ialrt.diataly clearing the harbor. Initially they wan in a line ahead fo& tioa but they ehanget to a line abreast foreration,whjah they avintaiaed. The x"Wi ntg surface vessel, which waa towing a target, proosow to a point south or the harbor entraamae whore it anchored. 3. The subaaaar'ines proceeded straight out into the bay and disappeared. um w then was of an old type. It looked Heir sad[ was a awe aodara type 7Nm bad no cars an a ere ok. than the others. It was 170 feet long. A. alaU gun was nlourated forimrd of the co=nning touter and a larger one, aft of the co=ning tower. The latter cou34 be trained laterally in a horizontal a rasnre. ~. Jost i side that barber eati'vaeel on the south side near Dfinam e, a destroyer of an old type with pennant iu*ber 14$0 lay at anchor. it was undatrlping repair. It van red-leaded in 80vWal p1a4es. Rsarby, on shore, were 50 s=ail.-ships of the samw type as the 20 described above. 6 - During the 2&4 hours that ship was in the harbor, no jet fighters were sewn tither an the gro or the air, but engine noise believed to be jet testing was heard esansting fray the field on several occasions. The only air traffic dbserred was two or three eeateatiaaral aircraft. 7. The inspectiazs upon arrival and departure were quite coal. There tid=e no formtIon on deck x w air search of the ship. Only ea=eras ant the-radio were sealed daring the stay in port. im AIR FIII AEC (Notes Washington distribution Indicated by "X"l Field distribution by "#" ) Approved For Release 2008/05/29: CIA-RDP80-0081 OA007400450002-2 Approved For Release 2008/05/29: CIA-RDP80-0081 OA007400450002-2 Approved For Release 2008/05/29: CIA-RDP80-0081 OA007400450002-2

Approved For Release 2008/05/29: CIA-RDP80-0081 OA007400450002-2 CENTRAL INTELLIGENCE AGENCY This material contains information affecting the National Defense of the United States within the meaning of the llspionage Laws. Title 18, U.B.C. Secs. 793 and 794, the transmission or revelation of which in any mapper to an uaauthorlaed person in prohibited by law. USSR (Lattrian .W) SUBJECT 1. Raval Activity at Riga 2. Jet Ingine Testing DATE OF INFO. PLACE ACQUIRED DATE ACQUIRED DATE DISTR. NO. OF PAGES REQUIREMENT NO. RD REFERENCES This is UNEVALUATED Information 1. While ship was waitiOg for a pilot off Riga as 12 *7 19gg bete 0330 and 1100, six aubasrines and 20 aril surface warships easrged tray the barb=. *ch of the snrfaae vessels was about 65 fast long and had ane gum an the foredeck and a canvas comet, ayliairiaal ob,ject an the gtiarterde k 2. Of these 20 Vessels, 19 of these pros e4st north ialrt.diataly clearing the harbor. Initially they wan in a line ahead fo& tioa but they ehanget to a line abreast foreration,whjah they avintaiaed. The x"Wi ntg surface vessel, which waa towing a target, proosow to a point south or the harbor entraamae whore it anchored. 3. The subaaaar'ines proceeded straight out into the bay and disappeared. um w then was of an old type. It looked Heir sad[ was a awe aodara type 7Nm bad no cars an a ere ok. than the others. It was 170 feet long. A. alaU gun was nlourated forimrd of the co=nning touter and a larger one, aft of the co=ning tower. The latter cou34 be trained laterally in a horizontal a rasnre. ~. Jost i side that barber eati'vaeel on the south side near Dfinam e, a destroyer of an old type with pennant iu*ber 14$0 lay at anchor. it was undatrlping repair. It van red-leaded in 80vWal p1a4es. Rsarby, on shore, were 50 s=ail.-ships of the samw type as the 20 described above. 6 - During the 2&4 hours that ship was in the harbor, no jet fighters were sewn tither an the gro or the air, but engine noise believed to be jet testing was heard esansting fray the field on several occasions. The only air traffic dbserred was two or three eeateatiaaral aircraft. 7. The inspectiazs upon arrival and departure were quite coal. There tid=e no formtIon on deck x w air search of the ship. Only ea=eras ant the-radio were sealed daring the stay in port. im AIR FIII AEC (Notes Washington distribution Indicated by "X"l Field distribution by "#" ) Approved For Release 2008/05/29: CIA-RDP80-0081 OA007400450002-2 Approved For Release 2008/05/29: CIA-RDP80-0081 OA007400450002-2 Approved For Release 2008/05/29: CIA-RDP80-0081 OA007400450002-2

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Jet engine being set up for testing