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 configuration with the nacelles off.
Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination At Mach Numbers from 0.3 to 2.9. Volume 7. Wing Net Chordwise Pressure Distributions and Isobars - Nacelles Off
1972
504 pages
Report
Keine Angabe
Englisch
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 , 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