Accession Number : AD0759192

Title :   Transpiration Cooling. Part III. User's Manual.

Descriptive Note : Final rept. 1 Jan 70-30 Nov 72,

Corporate Author : OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS

Personal Author(s) : Winget,Leon E. ; Han,L. S.

Report Date : MAR 1973

Pagination or Media Count : 190

Abstract : The computer program is presented for obtaining the drag and heat transfer coefficients around an airfoil with a blunt leading edge. The surface may be impermeable or porous with a specified blowing incorporating exponential profiles for both the velocity and temperature fields. The method has the capability of integrating around a body to the point at which the flow field separates from the surface. Provisions are included to handle the case of discontinuous blowing. In addition, any body for which the initial length can be approximated by the flat plate similarity solution can be analyzed. (Author)

Descriptors :   (*GAS TURBINE BLADES, *COOLING), AIR COOLED, BLADE AIRFOILS, LEADING EDGES, DRAG, HEAT TRANSFER, STAGNATION POINT, MATHEMATICAL MODELS, COMPUTER PROGRAMS, FLOW SEPARATION

Subject Categories : Jet and Gas Turbine Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE