Transpiration Cooling. Part III. User's Manual.

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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

Author(s):
Winget, Leon E. ; Han, L. S.
Author Organization(s):
OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS
Descriptive Note:
Final rept. 1 Jan 70-30 Nov 72,
Supplementary Note:
See also Part 2, AD-759 191. Paper copy available from NTIS $19.55/set of 3 reports as AD-759 190-SET.
Pagination:
0190

Security Markings

DOCUMENT & CONTEXTUAL SUMMARY

Distribution:
Approved For Public Release

RECORD

Collection: TR
Identifying Numbers
Report Number(s):
AFAPL-TR-73-11-Pt-3
Contract/Grant Number(s):
F33615-70-C-1331
Task Number(s):
306606
Project Number(s):
AF-3066, OSURF-2977
Monitor Series:
TR-73-11-Pt-3
 Subject Terms
Communities of Interest:
No COI(s) Identified
Descriptor(s):
(*GAS TURBINE BLADES, *COOLING), AIR COOLED, BLADE AIRFOILS, LEADING EDGES, DRAG, HEAT TRANSFER, STAGNATION POINT, MATHEMATICAL MODELS, COMPUTER PROGRAMS, FLOW SEPARATION
Field(s)/Group(s):
Jet and Gas Turbine Engines
Keyword(s):
COMPUTER AIDED ANALYSIS, *COOLING, *TRANSPIRATION
Report Date:
1973 Mar 01