Publication Date:
2019-07-13
Description:
A performance analysis of gas-driven shock tubes shows that transonic airfoil flows with chord Reynolds numbers in the range of 100 million can be generated behind the primary shock in a large shock tube. A study of flow over simple airfoils has been carried out at low and intermediate Reynolds numbers to assess the testing technique. Results obtained from schlieren photos and airfoil pressure measurements show that steady transonic flows similar to those observed for the airfoils in wind tunnels can be generated within the available testing time in a shock tube with either properly-contoured test section walls or a properly-designed slotted-wall test section. The study indicates that the shock tube is a useful facility for studying two-dimensional high Reynolds number transonic airfoil flows.
Keywords:
RESEARCH AND SUPPORT FACILITIES (AIR)
Type:
AIAA PAPER 78-769
,
Aerodynamic Testing Conference; Apr 19, 1978 - Apr 21, 1978; San Diego, CA
Format:
text
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