Mounted on a traversing mechanism on the tank upper Rotated to two positions to yield 128 pressureĬ) Three Chrysler miniature flow direction probes were
Line was instrumented with 64 pressure taps and was Pressure taps and was rotated to four positions to The L0 2 feedline was instrumented with 96 To fulfill these objectives the following steps were taken:Ī) Eight 3 -component balances were used to measure forcesī) 315 pressure orifices were distributed over all 9 above Objective was to obtain structural loads on the following Identified as IA190A/B and was conducted from 7 Feb. Launch vehicle in the NASA/Ames Research Center llxll-foot andĩx7-foot Unitary Plan Wind Tunnels. NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONĭata were obtained on a 3 -percent model of the Space Shuttle NAVIGATION, CONTROL & AERONAUTICS DIVISION
Prepared under NASA Contract Number NAS9-17840 SPACE SHUTTLE LAUNCH CONFIGURATION (MODEL 47-OTS) IN RESULTS OF EXPERIMENTAL INVESTIGATIONS TO DETERMINE Full text of " Results of experimental investigations to determine external tank protuberance loads using a 0.03-scale model of the Space Shuttle launch configuration (model 47-OTS) in the NASA/ARC unitary plan wind tunnel, volume 1"
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