This report presents the results of wind tunnel pressure distribution measurements made on a model of the Boeing supersonic transport configuration during design of the prototype airplanes. This volume contains wing upper and lower surface chordwise pressure distributions for the basic (nacelles on) configuration.
Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 4. Wing Chordwise Pressure Distributions - Nacelles on
1972
420 pages
Report
No indication
English
Aircraft , Fluid Mechanics , Aerodynamic loading , Supersonic aircraft , Aerodynamic control surfaces , Varying sweep wings , Jet transport planes , Experimental data , Graphics , Angle of attack , Mach number , Jet engine nacelles , Wind tunnel models , Airplane models , Pressure , Load distribution , Subsonic flow , Transonic flow , Supersonic flow , Delta wings , Design , Surfaces , Aircraft landings , Flaps(Control surfaces) , Trailing edge , Leading edge flaps , Deflection , Data processing , Interpolation , Mathematical prediction , Sst technology follow on program , Supersonic transports