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General Dynamics VEO (Vectored Engine Over Wing) designs

overscan

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General Dynamics "Short Snort"

[Removed image - better copy posted below]
 

hesham

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HI,

the General Dynamics V/STOL aircraft from 1980.
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19810014497_1981014497.pdf
 

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overscan

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Experimental Aerodynamic Characteristics of Two V/STOL Fighter/Attack Aircraft Configurations at Mach Numbers From 1.6 to 2.0
Walter P. Nelms, Donald A. Durston, and J. R. Lummus
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19810021545_1981021545.pdf

Experimental Aerodynamic Characteristics of Two V/STOL Fighter/Attack Aircraft Configurations at Mach Numbers From 0.4 to 1.4
Walter P. Nelrns, Donald A. Durston, Ames Research Center, Moffett Field, California
J. R. Lurnmus, General Dynamics, Fort Worth Division, Fort Worth, Texas
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19810006466_1981006466.pdf


E205 and R104 were derivatives of General Dynamics' Vectored-Engine-Over-Wing (VEO-Wing) concept studied under a Navy V/STOL fighter research contract in 1978.

E205 used a jet diffuser ejector concept and R104 the GE RALS (remote augmentation lift system) for VSTOL capability. They were chosen to represent the spread of cold/hot augmentation methods.
 

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hesham

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My dear Overscan,

and from NASA;

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19800024889_1980024889.pdf
 

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overscan

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Analysis of wind tunnel test results for a 9.39-per cent scale model of a VSTOL fighter/attack aircraft. Volume 1: Study overview
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19810014497_1981014497.pdf

Analysis of wind tunnel test results for a 9.39-per cent scale model of a VSTOL fighter/attack aircraft. Volume 3: Effects of configuration variations from baseline
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19810014499_1981014499.pdf

Analysis of wind tunnel test results for a 9.39-per cent scale model of a VSTOL fighter/attack aircraft. Volume 4: RALS R104 aerodynamic characteristics and comparisons with E205 configuration aerodynamic characteristics
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19810014500_1981014500.pdf
 

overscan

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Cross-posted from http://www.secretprojects.co.uk/forum/index.php/topic,1763.msg99157.html#msg99157
 

Stargazer2006

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The R-104 was one of two General Dynamics variants of the same basic design, submitted for the U.S. Navy's "Type B" VSTOL design competition. The R-104 used the "RALS" propulsion system while the E-205 used the "ejector" system.

Sources:

- STUDY FOR CONCEPTUAL DESIGN OF VEO-VTOL EXHAUST NOZZLE
- THE CONCEPTUAL DESIGN OF A VEO-VTOL EXHAUST NOZZLE — FINAL REPORT
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19800024889_1980024889.pdf

- ANALYSIS OF WIND TUNNEL TEST RESULTS FOR A 9.39-PER CENT SCALE MODEL OF A VSTOL FIGHTER/ATTACK AIRCRAFT — VOLUME I
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19810014497_1981014497.pdf
 

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Stargazer2006

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More on RALS:

The RALS concept has been proposed by General Electric as a means to supply a controllable forward lift vector in a V/STOL aircraft. The concept has been evaluated under contracts from the Naval Air Propulsion Center. These studies showed that, compared to propulsion systems using dedicated lift engines, the RALS ystem can provide about the same size (TOGW) supersonic fighter aircraft to complete the specified deck launched intercept mission. However, since all of the installed turbo-machinery is available to provide forward thrust, the RALS-powered aircraft far exceeds other concepts in terms of supersonic acceleration and combat specific energy, Ps. It also results in a much lower lifecycle cost because only one type of engine must be developed, procured, and maintained.

While these are important advantages, the RALS system does have disadvantages in that the remote augmentor is located near the pilot's compartment and electronics bay, requiring a means of local cooling, and it results in a relatively high exhaust gas temperature with potential deck heating problems. In theory, the use of an ejector nozzle in the remote system could pump sufficient ambient air to cool the surrounding aircraft bay and to mix the exhaust stream to a lower average footprint temperature. In addition, some degree of lift enhancement might be possible. In practice, the geometric constraint placed on the ejector for stowage and for low drag in the supersonic flight mode would make the use of a highly complex and highly efficient ejector quite difficult. However, if sufficient ejector action could be provided to increase the lift vector enough to offset the weight increase, the cooling advantages could still make the concept worthwhile.
Source: CONCEPTUAL DESIGN, EVALUATION AND RESEARCH IDENTIFICATION FOR REMOTE AUGMENTED PROPULSIVE LlFT SYSTEMS (RALS) WITH EJECTORS FOR VTOL AIRCRAFT
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19830004833_1983004833.pdf
 

Nik

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Makes you wonder if the P1127 / Harrier might have gone this route if the French ducted thrust patent had not worked out so well...
 

sferrin

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fightingirish said:
E-205 V/STOL wind-tunnel model, shown at the NASA's Ames Research Center 75th Anniversary Open House on October 18th, 2014.


Source (found via Overscan ;) ) : https://www.flickr.com/photos/gin_tonic/15478747750/in/set-72157649030746602
I would swear that shot of the model in the wind tunnel has been posted in another thread somewhere. I'm fairly certain I have it at home.
 

hesham

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ScrutorAudax said:
I found this at https://crgis.ndc.nasa.gov/historic/1146_Posters_and_Displays.
Nice find Scrutor.
 
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