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 comparisons of the results of the wing and horizontal stabilizer pressure measurements with the predictions of linear potential flow theory.
Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 2. Comparisons of Theory and Experiment
1972
488 pages
Report
No indication
English
Aircraft , Fluid Mechanics , Aerodynamic loading , Supersonic aircraft , Aerodynamic control surfaces , Aeroelasticity , Jet transport planes , Theory , Mathematical models , Experimental data , Wind tunnel models , Transonic characteristics , Delta wings , Stabilizers(Horizontal tail surface) , Pressure , Load distribution , Angle of attack , Deflection , Mathematical prediction , Uncertainty , Design , Airframes , Flaps(Control surfaces) , Jet engine nacelles , Subsonic flow , Wing body configurations , Thickness , Varying sweep wings , Airplane models , Supersonic flow , Graphics , Transonic flow , Hinge moments , Linear potential flow theory , Potential flow , Sst technology follow on program , Supersonic transports