Heat Transfer Rates on an Analytic Forebody in the AFWAL (Air Force Wright Aeronautical Laboratories) Mach 3 High Reynolds Number Wind Tunnel. Comparison of Test Results with Predictions from STAPAT (A Specific Thermal Analyzer Program for Aircraft Transparencies).
Abstract
This report describes a wind tunnel test program and the STAPAT computer program which were used to study heat transfer rates on an analytic forebody at Mach 3.0. STAPAT, a Specific Thermal Analyzer Program for Aircraft Transparencies, defines aerodynamic heating environments over windshields and canopies of high speed aircraft. STAPAT predictions were compared with measurements on an analytic forebody whose shape is representative of the forward fuselage of an aircraft. The measurements were obtained using a newly developed experimental technique for determining heat transfer rates at high Reynolds numbers and supersonic speeds in a cold flow wind tunnel. This technique incorporated a means for raising the temperature of the outer surface of the analytic forebody above the recovery temperature of the tunnel which was operated at stagnation temperatures near atmospheric. Heat transfer rates were significantly influenced by tunnel stagnation temperatures, gage surface temperatures and water temperatures. Use of a nondimensional heat transfer coefficient, the Stanton number, effectively eliminated heat transfer rate dependency upon these temperatures and therefore was shown to be the best way to evaluate heat transfer rates over the analytic forebody. The magnitudes of the measured heat transfer rates, their distribution over the analytic forebody and their good agreement with STAPAT calculations.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1988
- Accession Number
- ADA199523
Entities
People
- Charles A. Babish Iii.
- James R. Hayes
Organizations
- Wright Laboratory