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 integrated section and total surface characteristics for the wing.
Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 3. Wing Section and Total Surface Aerodynamic Coefficients
1972
464 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 , Pitch(Motion) , Moments , Design , Bending , Aircraft landings , Flaps(Control surfaces) , Deflection , Delta wings , Computer programs , Mathematical prediction , Interpolation , Data processing , Sst technology follow on program , Supersonic transports