"NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet" - Information and Links:

NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet - Info and Reading Options

"NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet" and the language of the book is English.


“NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet” Metadata:

  • Title: ➤  NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet
  • Author: ➤  
  • Language: English

Edition Identifiers:

  • Internet Archive ID: NASA_NTRS_Archive_20050177084

AI-generated Review of “NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet”:


"NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet" Description:

The Internet Archive:

Renewed interest in hypersonic propulsion systems has led to research programs investigating combined cycle engines that are designed to operate efficiently across the flight regime. The Rocket-Based Combined Cycle Engine is a propulsion system under development at the NASA Lewis Research Center. This engine integrates a high specific impulse, low thrust-to-weight, airbreathing engine with a low-impulse, high thrust-to-weight rocket. From takeoff to Mach 2.5, the engine operates as an air-augmented rocket. At Mach 2.5, the engine becomes a dual-mode ramjet; and beyond Mach 8, the rocket is turned back on. One Rocket-Based Combined Cycle Engine variation known as the "Strut-Jet" concept is being investigated jointly by NASA Lewis, the U.S. Air Force, Gencorp Aerojet, General Applied Science Labs (GASL), and Lockheed Martin Corporation. Work thus far has included wind tunnel experiments and computational fluid dynamics (CFD) investigations with the NPARC code. The CFD method was initiated by modeling the geometry of the Strut-Jet with the GRIDGEN structured grid generator. Grids representing a subscale inlet model and the full-scale demonstrator geometry were constructed. These grids modeled one-half of the symmetric inlet flow path, including the precompression plate, diverter, center duct, side duct, and combustor. After the grid generation, full Navier-Stokes flow simulations were conducted with the NPARC Navier-Stokes code. The Chien low-Reynolds-number k-e turbulence model was employed to simulate the high-speed turbulent flow. Finally, the CFD solutions were postprocessed with a Fortran code. This code provided wall static pressure distributions, pitot pressure distributions, mass flow rates, and internal drag. These results were compared with experimental data from a subscale inlet test for code validation; then they were used to help evaluate the demonstrator engine net thrust.

Read “NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet”:

Read “NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet” by choosing from the options below.

Available Downloads for “NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet”:

"NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet" is available for download from The Internet Archive in "texts" format, the size of the file-s is: 1.09 Mbs, and the file-s went public at Fri Oct 14 2016.

Legal and Safety Notes

Copyright Disclaimer and Liability Limitation:

A. Automated Content Display
The creation of this page is fully automated. All data, including text, images, and links, is displayed exactly as received from its original source, without any modification, alteration, or verification. We do not claim ownership of, nor assume any responsibility for, the accuracy or legality of this content.

B. Liability Disclaimer for External Content
The files provided below are solely the responsibility of their respective originators. We disclaim any and all liability, whether direct or indirect, for the content, accuracy, legality, or any other aspect of these files. By using this website, you acknowledge that we have no control over, nor endorse, the content hosted by external sources.

C. Inquiries and Disputes
For any inquiries, concerns, or issues related to the content displayed, including potential copyright claims, please contact the original source or provider of the files directly. We are not responsible for resolving any content-related disputes or claims of intellectual property infringement.

D. No Copyright Ownership
We do not claim ownership of any intellectual property contained in the files or data displayed on this website. All copyrights, trademarks, and other intellectual property rights remain the sole property of their respective owners. If you believe that content displayed on this website infringes upon your intellectual property rights, please contact the original content provider directly.

E. Fair Use Notice
Some content displayed on this website may fall under the "fair use" provisions of copyright law for purposes such as commentary, criticism, news reporting, research, or educational purposes. If you believe any content violates fair use guidelines, please reach out directly to the original source of the content for resolution.

Virus Scanning for Your Peace of Mind:

The files provided below have already been scanned for viruses by their original source. However, if you’d like to double-check before downloading, you can easily scan them yourself using the following steps:

How to scan a direct download link for viruses:

  • 1- Copy the direct link to the file you want to download (don’t open it yet).
    • (a free online tool) and paste the direct link into the provided field to start the scan.
  • 2- Visit VirusTotal (a free online tool) and paste the direct link into the provided field to start the scan.
  • 3- VirusTotal will scan the file using multiple antivirus vendors to detect any potential threats.
  • 4- Once the scan confirms the file is safe, you can proceed to download it with confidence and enjoy your content.

Available Downloads

  • Source: Internet Archive
  • Internet Archive Link: Archive.org page
  • All Files are Available: Yes
  • Number of Files: 12
  • Number of Available Files: 12
  • Added Date: 2016-10-14 13:28:09
  • PPI (Pixels Per Inch): 300
  • OCR: ABBYY FineReader 11.0

Available Files:

1- Text PDF

  • File origin: original
  • File Format: Text PDF
  • File Size: 0.00 Mbs
  • File Name: NASA_NTRS_Archive_20050177084.pdf
  • Direct Link: Click here

2- Metadata

  • File origin: original
  • File Format: Metadata
  • File Size: 0.00 Mbs
  • File Name: NASA_NTRS_Archive_20050177084_files.xml
  • Direct Link: Click here

3- Metadata

  • File origin: original
  • File Format: Metadata
  • File Size: 0.00 Mbs
  • File Name: NASA_NTRS_Archive_20050177084_meta.sqlite
  • Direct Link: Click here

4- Metadata

  • File origin: original
  • File Format: Metadata
  • File Size: 0.00 Mbs
  • File Name: NASA_NTRS_Archive_20050177084_meta.xml
  • Direct Link: Click here

5- Item Tile

  • File origin: original
  • File Format: Item Tile
  • File Size: 0.00 Mbs
  • File Name: __ia_thumb.jpg
  • Direct Link: Click here

6- Animated GIF

  • File origin: derivative
  • File Format: Animated GIF
  • File Size: 0.00 Mbs
  • File Name: NASA_NTRS_Archive_20050177084.gif
  • Direct Link: Click here

7- Abbyy GZ

  • File origin: derivative
  • File Format: Abbyy GZ
  • File Size: 0.00 Mbs
  • File Name: NASA_NTRS_Archive_20050177084_abbyy.gz
  • Direct Link: Click here

8- DjVuTXT

  • File origin: derivative
  • File Format: DjVuTXT
  • File Size: 0.00 Mbs
  • File Name: NASA_NTRS_Archive_20050177084_djvu.txt
  • Direct Link: Click here

9- Djvu XML

  • File origin: derivative
  • File Format: Djvu XML
  • File Size: 0.00 Mbs
  • File Name: NASA_NTRS_Archive_20050177084_djvu.xml
  • Direct Link: Click here

10- Single Page Processed JP2 ZIP

  • File origin: derivative
  • File Format: Single Page Processed JP2 ZIP
  • File Size: 0.00 Mbs
  • File Name: NASA_NTRS_Archive_20050177084_jp2.zip
  • Direct Link: Click here

11- Scandata

  • File origin: derivative
  • File Format: Scandata
  • File Size: 0.00 Mbs
  • File Name: NASA_NTRS_Archive_20050177084_scandata.xml
  • Direct Link: Click here

12- Archive BitTorrent

  • File origin: metadata
  • File Format: Archive BitTorrent
  • File Size: 0.00 Mbs
  • File Name: NASA_NTRS_Archive_20050177084_archive.torrent
  • Direct Link: Click here

Search for “NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet” downloads:

Visit our Downloads Search page to see if downloads are available.

Find “NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet” in Libraries Near You:

Read or borrow “NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet” from your local library.

Buy “NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet” online:

Shop for “NASA Technical Reports Server (NTRS) 20050177084: Computational Fluid Dynamics Analysis Method Developed For Rocket-Based Combined Cycle Engine Inlet” on popular online marketplaces.