Pressure Distributions on a Flat-plate Delta Wing Swept 65 Deg at a Mach Number of 5.97 at Angles of Attack from 65 Deg to 115 Deg and Angles of Roll from 0 Deg to 25 Deg at a 90 Deg Angle of Attack

Pressure Distributions on a Flat-plate Delta Wing Swept 65 Deg at a Mach Number of 5.97 at Angles of Attack from 65 Deg to 115 Deg and Angles of Roll from 0 Deg to 25 Deg at a 90 Deg Angle of Attack
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Publisher:
Total Pages: 32
Release: 1962
Genre:
ISBN:

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Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9

Experimental Pressure Distributions Over Wing Tips at Mach Number 1.9
Author: Harold Mirels
Publisher:
Total Pages: 28
Release: 1949
Genre: Aerodynamic load
ISBN:

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An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.