Pressure Distribution Measurements of Swept-back Wings (Second Report on Swept-back Wings) PDF Download
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Author: H. Luetgebrune Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 35
Book Description
Pressure distribution measurements were carried out on a straight wing, a strongly swept-back wing, and on a strongly swept forward wing. The experimental results were compared with Multhopp's theoretical lift distribution.
Author: H. Luetgebrune Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 35
Book Description
Pressure distribution measurements were carried out on a straight wing, a strongly swept-back wing, and on a strongly swept forward wing. The experimental results were compared with Multhopp's theoretical lift distribution.
Author: W. Jacobs Publisher: ISBN: Category : Airplanes Languages : en Pages : 19
Book Description
This report presents comprehensive pressure-distribution measurements on four (4) swept-back wings (phi = 0 deg, 15 deg, 30 deg, and 45 deg) of constant chord and over a large range of angles of attack with symmetrical air flow. The distributions, experimentally obtained, were compared with theoretical ones calculated by the methods of Weissinger and Multhopp.
Author: Edward C. B. Danforth Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 42
Book Description
Measurements of pressure were made over the chord of a swept-wing model at four stations along (2, 6, 50, and 82 percent semispan) by the NACA wing-flow method. The model tested was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. The tests were conducted at Mach numbers from about 0.7 to 1.1 at angles of attack from -1 to 4 degrees. The Reynolds number of the tests was nominally 600,000 based on the wing chord in the stream direction. The results are presented to show the chordwise pressure distributions and the spanwise distributions of section lift, drag, and pitching moment.
Author: A. Thiel Publisher: ISBN: Category : Airplanes Languages : en Pages : 5
Book Description
The spanwise lift-distribution measurements in straight air flow on a straight and a 35 deg swept-back tapered wing (NACA airfoil section 0012) are compared with theory for two angles of attack each (alpha approx. 6 deg and alpha approx. 12 deg) in the unstalled range of flow. The complete pressure distribution for the greater of the two angles is indicated.
Author: H. Luetgebrune
Author: H. Luetgebrune
Author: W. Jacobs
Author: J. Weber
Author: P. Calvin Stainback
Author: Edward C. B. Danforth
Author: A. Thiel
Author: College of Aeronautics (Cranfield, Bedfordshire)
Author: Victor Montague Falkner
Author: Victor Montague Falkner
Author: Arthur William Babister