Basic aerodynamic and heat transfer studies for spacecraft boosters in prelaunch conditions
Miller, L. Scott
Miller, L. Scott
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1994
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Miller, L. (1994). Basic aerodynamic and heat transfer studies for spacecraft boosters in prelaunch conditions. Journal of Spacecraft and Rockets, 31(4), 585-591.
Abstract
A basic experimental investigation was conducted on a simple tandem three-cylinder model to identify potential atmospheric aerodynamic and thermodynamic effects on a typical spacecraft booster configuration during prelaunch conditions. Testing was conducted in a low-speed wind tunnel at a Reynolds number of 100,000. The center and aft cylinders were cooled and heated, respectively, to allow for sustained heat transfer. Flow visualization, anemometry, static pressure, and heat flux measurements were obtained. Results indicate that the model flowfield behavior is very complex and that notable aerodynamic interactions between model elements occur. Most significantly, flow is observed to recirculate about both the cool center and warm aft cylinders. Convective heat transfer maxima were correlated with the identified aerodynamic features. The azimuthal average center and aft cylinder Nusseit-number behavior was found to differ by only about 10%. © 1992 by the American Institute of Aeronautics and Astronautics, Inc.
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American Institute of Aeronautics and Astronautics Inc.
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Journal of Spacecraft and Rockets
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00224650