Accession Number:

AD0420907

Title:

AN INVESTIGATION OF A HYPERSONIC CASCADE WITH 120 DEGREES TURNING PASSAGES,

Descriptive Note:

Corporate Author:

POLYTECHNIC INST OF BROOKLYN N Y

Report Date:

1963-06-01

Pagination or Media Count:

70.0

Abstract:

A series of hypersonic compressor blades were designed by the method of characteristics, for flow turning angles of approximately 120 degrees and leading edges with included angles of 15 degrees. The blade designs correspond to an in-let flow angle of 60 degrees and relative Mach numbers of 4.5, 6.0, 8.0, and 12.0. The resulting pressure recovery and discharge Mach number in the passage exit are presented in addition to the static pressure and heat transfer distributions along the blade surfaces. Tables of the blade coordinates are also included. An experimental investigation of the flow in a cascade model at a free stream Mach number of 4.4 has been performed. The experimental results are compared to the analytical predictions and are shown to agree reasonably well. The effect of blunting the leading edges of the blades has also been studied. The major effect observed is that the pressure recovery decreases with increasing nose radius the static pressure and heat transfer on the blades as well as the Mach number in the passage exit are essentially unaffected. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE