CALCULATED HEAT TRANSFER AND COOLING SYSTEM PERFORMANCE, VOLUME 1
GENERAL ELECTRIC CO CINCINNATI OH ADVANCED ENGINE AND TECHNOLOGY DEPT
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Based on analysis and limited test data, the aircraft cooling and structural protection systems are believed to have sufficient performance capability to permit orderly conduct of Installed System Functional, NASA-Ames 40 x 80 Wind Tunnel, and Edwards Air Force Base Flight Test Programs even though externally induced environmental temperatures to 1040F develop during fan mode operation. Occasional local and minor overheating problems are expected within the broad range of possible operating conditions however, it is expected they can be overcome with minor structural modifications, installation of additional insulation, andor minor modification of operational procedures. Lack of detailed knowledge of the externally induced environment made cooling and structural systems designs and analysis difficult. In an attempt to gain further insight to this complex problem, a procedure was developed whereby existing literature data on downwash phenomena could be applied quantitatively to the XV-5A induced environment. Results show directional effects of aircraft control settings, and indicate the strong possibility of hot gas ingestion by the engine and cooling system air inlet. These results also indicate means whereby adverse effects may be minimized or eliminated.
- Research and Experimental Aircraft