Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 8. Wing Chordwise Pressure Distributions, Effect of: Nacelles, Flaps, Spoilers, Sideslip, and Reynolds Number. Part 2
1972
247 pages
Report
Keine Angabe
Englisch
Aircraft , Fluid Mechanics , Aerodynamic loading , Supersonic aircraft , Aerodynamic control surfaces , Varying sweep wings , Jet transport planes , Experimental data , Graphics , Jet engine nacelles , Flaps(Control surfaces) , Spoilers , Sideslip , Reynolds number , Subsonic flow , Transonic flow , Supersonic flow , Angle of attack , Mach number , Wind tunnel models , Airplane models , Design , Wing body configurations , Pressure , Load distribution , Leading edge flaps , Trailing edge , Deflection , Airspeed , Braking , Delta wings , Data processing , Interpolation , Mathematical prediction , Flaperons , Speed brakes , Sst technology follow on program , Supersonic transports
Engineering Index Backfile | 1948
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