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 vertical tail net chordwise pressure distributions and isobars showing the effect of sideslip and rudder deflections.
Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. volume 12. Vertical Tail Net Chordwise Pressure Distributions and Isobars
1972
488 pages
Report
No indication
English
Aircraft , Fluid Mechanics , Aerodynamic loading , Supersonic aircraft , Aerodynamic control surfaces , Aerial rudders , Jet transport planes , Experimental data , Graphics , Tails(Aircraft) , Deflection , Sideslip , Mach number , Wind tunnel models , Airplane models , Design , Pressure , Load distribution , Subsonic flow , Transonic flow , Supersonic flow , Jet engine nacelles , Data processing , Interpolation , Mathematical prediction , Sst technology follow on program , Supersonic transports