Aerothermodynamic aspects of shock-interference patterns for shuttleconfigurations during entry-Reference-Cited by-同舟云学术

Aerothermodynamic aspects of shock-interference patterns for shuttleconfigurations during entry

Published:1973-01-10 Issue: Volume: Page:
ISSN:
Container-title:11th Aerospace Sciences Meeting
language:
Short-container-title:

Author:

BERTIN J.¹,GRAUMANN B.¹,GOODRICH W.²

Affiliation:

1. Texas, University, Austin, Tex.

2. NASA, Manned Spacecraft Center, Houston, Tex.

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1973-238

Reference27 articles.

1. P IC) NAR 1618 DWO

2. Delta-wing Configurations M,= 10.61

3. zr = 0.55b. and (3) at zr = 0.75b. The first peak is attributed to an interaction between boundary layer and a "lambda" shock.ofthe compression corner. which were evident in the flow-field photographs 8 of the flow in the compression corner created by the wing-root fairing on the NAR 134 model, are sketched in Fig. 7. The heat-transfer perturbation which occurred at the thermocouple located where these waves intersect the wing leading-edge appears to be limited to a small region near the leading edge.Thesecond peak was recorded by the thennocoup1.elocated where the curve defining the intersection of the two shock surfaces crossed the wing leading-edge (flow-field feature number 5 of Fig. occured in the region downstream of this thennocouple, as can be seen in the heat-transfer contout's of Fig. 7. The "streamline" arrow is based on the oil-streak patterns of Clearye. rate measured at zr = 0.75b appears to be relatively high because the heating rates at the adjacent thermocouples are actually relatively low. These relatively low heating rates are attributed to the expansion waves associated with the Type VI interference pattern.

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1. Defining the Aerothermodynamic Methodology;Hypersonics;1989