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4. Cones in Supersonic Flow

Author

Hantzsche, W and Wendt, H

Subjects
Aerodynamics
Abstract

In the case of cones in axially symmetric flow of supersonic velocity, adiabatic compression takes place between shock wave and surface of the cone. Interpolation curves betwen shock polars and the surface are therefore necessary for the complete understanding of this type of flow. They are given in the present report by graphical-numerical integration of the differential equation for all cone angles and airspeeds.

Published
1947

5. The Compressible Potential Flow Past Elliptic Symmetrical Cylinders at Zero Angle of Attack and with No Circulation

Author

Hantzsche, W and Wendt, H

Subjects
Fluid Mechanics And Thermodynamics
Abstract

For the tunnel corrections of compressible flows those profiles are of interest for which at least the second approximation of the Janzen-Rayleigh method can be applied in closed form. One such case is presented by certain elliptical symmetrical cylinders located in the center of a tunnel with fixed walls and whose maximum velocity, incompressible, is twice the velocity of flow. In the numerical solution the maximum velocity at the profile and the tunnel wall as well as the entry of sonic velocity is computed. The velocity distribution past the contour and in the minimum cross section at various Mach numbers is illustrated on a worked out-example.

Published
1942

9. THE LAMINAR BOUNDARY LAYER ON A CONE IN A SUPERSONIC AIR STREAM AT ZERO ANGLE OF ATTACK

Author

RAND CORP SANTA MONICA CA, Hantzsche, W, Wendt, H, RAND CORP SANTA MONICA CA, Hantzsche, W, and Wendt, H

Abstract

This report demonstrates that the integration of the equations for the laminar boundary layer on a cone in a supersonic air stream can be reduced to the equations for the flat plate. The simple result is obtained, that on the cone the boundary layer is different by 1/square root of 3 as compared to the plate. The mean friction coefficient and the heat transfer coefficient are greater by the factor 2/3 times the square root of 3., Trans. of mono. die Laminare Grenzschicht bei einem mit Uberschallgeschwindigkeit Angestromtem Nichtangestellten Kreiskegel, n.p., n.d.

Published
1947

10. The Compressible Potential Flow Past Elliptic Symmetrical Cylinders at Zero Angle of Attack and with No Circulation

Author

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC, Hantzsche, W., Wendt, H., NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC, Hantzsche, W., and Wendt, H.

Abstract

A group of profiles is investigated, which are of interest for the wind tunnel corrections of compressible flows and which allow application of - at least - the second approximation of the Janzen-Rayleigh method in closed form. The profiles in question are ellipsoidal symmetrical cylinders, located In the center of a tunnel with fixed walls, which have - in incompressible flow - for each thickness ratio double the flow velocity as maximum velocity. In the numerical solution, the maximum velocity at the profile and the tunnel wall as well as the entry of sonic velocity is computed., Translated from Die kompressible Potentialstroemung um eine Schar von nichtangestellten symmetrischen Zylindern im Kanal, prepared by Luftfahrtforschung, Germany (East and West), v18 n9 p311-316, 20 Sep 1941. Text in English.

Published
1942

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