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 nacelles-off configuration.
Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 6. Wing Chordwise Pressure Distribution - Nacelles Off
1972
390 pages
Report
No indication
English
Aircraft , Fluid Mechanics , Aerodynamic loading , Supersonic aircraft , Aerodynamic control surfaces , Varying sweep wings , Jet transport planes , Experimental data , Graphics , Flaps(Control surfaces) , Subsonic flow , Transonic flow , Supersonic flow , Angle of attack , Mach number , Wind tunnel models , Airplane models , Pressure , Load distribution , Leading edge flaps , Trailing edge , Deflection , Design , Delta wings , Mathematical prediction , Interpolation , Data processing , Sst technology follow on program , Supersonic transports