The results of tests of 22 triangular wings, representing two leading-edge shapes for each of 11 apex angles, at Mach numbers 1.62, 1.92, and 1.40 are presented and compared with theory. All wings have a common thickness ratio of 8 percent and a common maximum-thickness point at 18 percent chord. Lift, drag, and pitching moment are given for all wings at each Mach number. The relation of transition in the boundary layer, shocks on the wing surfaces, and characteristics of the pressure distributions is discussed for several wings.
Investigations at Supersonic Speeds of 22 Triangular Wings Representing Two Airfoil Sections for Each of 11 Apex Angles
1955-01-01
Sonstige
Keine Angabe
Englisch
Engineering Index Backfile | 1955
|Stability derivatives of triangular wings at supersonic speeds
Engineering Index Backfile | 1948
|Stability derivatives of triangular wings at supersonic speeds
Engineering Index Backfile | 1948
|