"Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations" - Information and Links:

Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations - Info and Reading Options

"Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations" and the language of the book is English.


“Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations” Metadata:

  • Title: ➤  Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations
  • Authors:
  • Language: English

“Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations” Subjects and Themes:

Edition Identifiers:

  • Internet Archive ID: nasa_techdoc_19870001396

AI-generated Review of “Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations”:


"Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations" Description:

The Internet Archive:

This paper describes methodology and an associated computer program for the design of wing lifting surfaces with attainable thrust taken into consideration. The approach is based on the determination of an optimum combination of a series of candidate surfaces rather than the more commonly used candidate loadings. Special leading-edge surfaces are selected to provide distributed leading-edge thrust forces which compensate for any failure to achieve the full theoretical leading-edge thrust, and a second series of general candidate surfaces is selected to minimize drag subject to constraints on the lift coefficient and, if desired, on the pitching moment coefficient. A primary purpose of the design approach is the introduction of attainable leading-edge thrust considerations so that relatively mild camber surfaces may be employed in the achievement of aerodynamic efficiencies comparable to those attainable if full theoretical leading-edge thrust could be achieved. The program provides an analysis as well as a design capability and is applicable to both subsonic and supersonic flow.

Read “Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations”:

Read “Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations” by choosing from the options below.

Available Downloads for “Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations”:

"Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations" is available for download from The Internet Archive in "texts" format, the size of the file-s is: 16.14 Mbs, and the file-s went public at Wed Jul 21 2010.

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: 13
  • Number of Available Files: 13
  • Added Date: 2010-07-21 11:47:45
  • PPI (Pixels Per Inch): 400
  • OCR: ABBYY FineReader 8.0

Available Files:

1- Text PDF

  • File origin: original
  • File Format: Text PDF
  • File Size: 0.00 Mbs
  • File Name: 19870001396.pdf
  • Direct Link: Click here

2- Metadata

  • File origin: original
  • File Format: Metadata
  • File Size: 0.00 Mbs
  • File Name: 19870001396.pdf_meta.txt
  • Direct Link: Click here

3- JPEG Thumb

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

4- Metadata

  • File origin: original
  • File Format: Metadata
  • File Size: 0.00 Mbs
  • File Name: nasa_techdoc_19870001396_files.xml
  • Direct Link: Click here

5- Metadata

  • File origin: original
  • File Format: Metadata
  • File Size: 0.00 Mbs
  • File Name: nasa_techdoc_19870001396_meta.xml
  • Direct Link: Click here

6- DjVu

  • File origin: derivative
  • File Format: DjVu
  • File Size: 0.00 Mbs
  • File Name: 19870001396.djvu
  • Direct Link: Click here

7- Animated GIF

  • File origin: derivative
  • File Format: Animated GIF
  • File Size: 0.00 Mbs
  • File Name: 19870001396.gif
  • Direct Link: Click here

8- Abbyy GZ

  • File origin: derivative
  • File Format: Abbyy GZ
  • File Size: 0.00 Mbs
  • File Name: 19870001396_abbyy.gz
  • Direct Link: Click here

9- DjVuTXT

  • File origin: derivative
  • File Format: DjVuTXT
  • File Size: 0.00 Mbs
  • File Name: 19870001396_djvu.txt
  • Direct Link: Click here

10- Djvu XML

  • File origin: derivative
  • File Format: Djvu XML
  • File Size: 0.00 Mbs
  • File Name: 19870001396_djvu.xml
  • Direct Link: Click here

11- Single Page Processed JP2 ZIP

  • File origin: derivative
  • File Format: Single Page Processed JP2 ZIP
  • File Size: 0.01 Mbs
  • File Name: 19870001396_jp2.zip
  • Direct Link: Click here

12- Scandata

  • File origin: derivative
  • File Format: Scandata
  • File Size: 0.00 Mbs
  • File Name: 19870001396_scandata.xml
  • Direct Link: Click here

13- Archive BitTorrent

  • File origin: metadata
  • File Format: Archive BitTorrent
  • File Size: 0.00 Mbs
  • File Name: nasa_techdoc_19870001396_archive.torrent
  • Direct Link: Click here

Search for “Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations” downloads:

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

Find “Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations” in Libraries Near You:

Read or borrow “Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations” from your local library.

Buy “Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations” online:

Shop for “Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations” on popular online marketplaces.



Find "Numerical Methods And A Computer Program For Subsonic And Supersonic Aerodynamic Design And Analysis Of Wings With Attainable Thrust Considerations" in Wikipdedia