Results 121 to 130 of about 31,952 (223)

Boundary layer, skin friction, and boattail pressure measurements from the YF-12 airplane at Mach numbers up to 3 [PDF]

open access: yes, 1978
In-flight measurements of boundary layer and skin friction data were made on YF-12 airplanes for Mach numbers between 2.0 and 3.0. Boattail pressures were also obtained for Mach numbers between 0.7 and 3.0 with Reynolds numbers up to four hundred million.
Fisher, D. F.
core   +1 more source

Fatigue tests on big structure assemblies of concorde aircraft [PDF]

open access: yes
Fatigue tests on structural assemblies of the Concorde supersonic transport aircraft are reported. Two main sections of the aircraft were subjected to pressure, mechanical load, and thermal static tests.
Nguyen, V. P., Perrais, J. P.
core   +1 more source

Enhancement of thrust reverser cascade performance using aerodynamic and structural integration [PDF]

open access: yes, 2004
This paper focuses on the design of a cascade within a cold stream thrust reverser during the early, conceptual stage of the product development process.
Armstrong, Cecil   +7 more
core  

Flight propulsion control integration for V/STOL aircraft [PDF]

open access: yes
The goal of the propulsion community is to have the enabling propulsion technologies in place to permit a low risk decision regarding the initiation of a research STOVL supersonic attack fighter aircraft in the mid-1990's.
Mihaloew, James R.
core   +1 more source

Supersonic aircraft

open access: yes, 2011
Sychova, I.U., Zolotova, E.I.
openaire   +2 more sources

Installation Effects in Supersonic Aircrafts

open access: yes, 2016
Validerat; 20160414 (global_studentproject_submitter)
openaire   +1 more source

Powered-lift aircraft technology [PDF]

open access: yes
Powered lift aircraft have the ability to vary the magnitude and direction of the force produced by the propulsion system so as to control the overall lift and streamwise force components of the aircraft, with the objective of enabling the aircraft to ...
Deckert, W. H., Franklin, J. A.
core   +1 more source

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