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Thermal/structural analyses of several hydrogen-cooled leading-edge concepts for hypersonic flight vehicles

Author:
Mockler, Theodore T.
Published:
JAN 1, 1990.
Physical Description:
1 electronic document
Additional Creators:
Gladden, Herbert J., Tong, Mike, and Melis, Matthew E.
Online Version

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Summary:
The aerodynamic heating at high flight Mach numbers, when shock interference heating is included, can be extremely high and can exceed the capability of most conventional metallic and potential ceramic materials available. Numerical analyses of the heat transfer and thermal stresses are performed on three actively cooled leading-edge geometries (models) made of three different materials to address the issue of survivability in a hostile environment. These analyses show a mixture of results from one configuration to the next. Results for each configuration are presented and discussed. Combinations of enhanced internal film coefficients and high material thermal conductivity of copper and tungsten are predicted to maintain the maximum wall temperature for each concept within acceptable operating limits. The exception is the TD nickel material which is predicted to melt for most cases. The wide range of internal impingement film coefficients (based on correlations) for these conditions can lead to a significant uncertainty in expected leading-edge wall temperatures. The equivalent plastic strain, inherent in each configuration which results from the high thermal gradients, indicates a need for further cyclic analysis to determine component life.
Other Subject(s):
Collection:
NASA Technical Reports Server (NTRS) Collection.
Note:
Document ID: 19900005195.
Accession ID: 90N14511.
E-4788.
NASA-TM-102391.
NAS 1.15:102391.
AIAA PAPER 90-0053.
Aerospace Sciences Meeting; 8-11 Jan. 1990; Reno, NV; United States.
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No Copyright.
View MARC record | catkey: 15687909