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 net chordwise pressure distributions and isobars 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 5. Wing Net Chordwise Pressure distribution and Isobars - Nacelles on. Part 1
1972
277 pages
Report
Keine Angabe
Englisch
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 , Pressure , Load distribution , Subsonic flow , Transonic flow , Delta wings , Design , Aircraft landings , Flaps(Control surfaces) , Leading edge flaps , Trailing edge , Deflection , Sst technology follow on program , Supersonic transports