Actions for Basic Pressure Measurements at Transonic Speeds on a Thin 45 deg Sweptback highly Tapered Wing With Systematic Spanwise Twist Variations

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Basic Pressure Measurements at Transonic Speeds on a Thin 45 deg Sweptback highly Tapered Wing With Systematic Spanwise Twist Variations

Author
Mugler, John P., Jr.
Published
Apr. 1959.
Physical Description
1 electronic document
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary
Pressure distributions obtained in the Langley 8-foot transonic pressure tunnel on a thin highly tapered twisted 45 deg sweptback wing-body combination are presented. The wing has a quadratic spanwise twist variation from 0 deg at 10 percent of the semispan to 6 deg at the tip. The tip is at a lower angle of attack than the root. Tests were made at stagnation pressures of both 0.5 and 1.0 atmosphere at Mach numbers from 0.800 to 1.200 through an angle-of-attack range from -4 deg to 20 deg.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19980230683.
L-207.
NASA-MEMO-2-24-59L.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15644239