Low-speed wind-tunnel investigation of a triangular sweptback air inlet in the root of a 45 degree sweptback wing /
Arvid L. Keith, Jr., and Jack Schiff.
Description
- Language(s)
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English
- Published
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Washington, D.C. : National Advisory Committee for Aeronautics, 1950.
- Summary
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Installation of the wing-root inlet was accomplished with no significant effects on the force characteristics of the basic wing. The fuselage boundary layer entering the inlet was thin and required no boundary-layer-control device ahead of the inlet. Near unity inlet total-pressure recovery was obtained to about 86 percent of the maximum lift coefficient over a large range of inlet-velocity ratio. Maximum local velocities over the external surfaces of the inlet sections were no greater than those over the wing at a midspan station for the assumed high-speed operating conditions.
A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root.
- Note
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NACA Research Memorandum L50I01.
"November 6, 1950."
Title from cover.
- Physical Description
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71 p. :
ill. ;
27 cm.
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