Theoretical and experimental cascade flow investigations at high subsonic Mach numbers /
U. Hopkes.

Description

Main Author

Hopkes, U.

Related Names

United States. Air Force.

Language(s)

English

Published

[Washington, D.C.] : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1959.

Subjects

Turbines > Turbines / Blades.
Cascades (Fluid dynamics)
Air flow.
Cascades (Fluid dynamics)
Air flow.
Turbines > Turbines / Blades.

Summary

Extensive experimental investigations on two-dimensional cascades at high subsonic Mach numbers have been carried out in the Variable Density High Speed Cascade Wind Tunnel of the Deutsche Forschungsanstalt fur Luftfahrt, Braunschweig. Varying the cascade geometry and the Mach number the following quantities have been measured up to the choking Mach number for two different blade profiles (NACA 0010 and NACA 8410): pressure distribution on the blade, loss coefficient, deflection of flow and static pressure difference across the cascade. The loss coefficient and the deflection are nearly constant up to the critical Mach number, but the static pressure difference varies with the Mach number. The experimental pressure distributions have been compared with different theoretical methods for calculating pressure distributions in compressible flow.

Note

Research supported by the United States Air Force performed through the European Office Air Research Development Command by Institut fur Aerodynamik der Deutschen Forschungsanstalt fur Luftfahrt.
ASTIA Document No. AD 214 810.
"Braunschweig, June 26, 1959."

Physical Description

[2], 55 pages : illustrations ; 28 cm.

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