Predicted Acoustic and Aerodynamic Noise Environments for the Reusable Space Shuttle Orbiter

Abstract

Aeroacoustic noise generated by the proposed shuttle vehicle was predicted for various orbiter locations. Over-all SPL of 162–163 dB was calculated for shuttle liftoff, using Saturn V liftoff data and a scaling relationship based on the Eldred method. Over-all SPL of 167 dB was determined for the flow interference region between the mated booster and orbiter during the qmax period of ascent, using wind tunnel data obtained by Coe, Dods, and Robinson and flight data measured on Titan IIIC. Aerodynamic noise of 158 dB was predicted during ascent for regions immediately before and behind the cockpit using wind tunnel data provided by Coe and by Stevens, and for the mid- and aft fuselage using procedures developed by Bies and by Ailman, as well as Saturn V flight data. Maximum entry levels of 139–144 dB were estimated using separate procedures developed by Ailman, Bies, and Heller and Holmes.