Pressure-distribution Measurements on a Straight and on a 35 Degree Swept-back Tapered Wings PDF Download
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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: 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 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: A. Thiel
Author: A. Thiel
Author: G. Thiel
Author: H. Luetgebrune
Author: W. Jacobs
Author: J. Black
Author: 
Author: J. Weber
Author: 
Author: Joseph Black
Author: P. Calvin Stainback