Transonic Wind-Tunnel Investigation of the Fin Loads on a 1/8-Scale Model Simulating the First Stage of the Scout Research Vehicle (English Edition)

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An gallup to determine the fin loads on a 1/8-scale model simulating the first séjour of the Boy-scout research vehicle was made in the Langley 8-foot transonic catacombe at Mach numbers from 0.40 to 1.20. Tests were conducted over an détour-of-attack range from embout -10 to 10 deg and at a Reynolds number per foot of approximately 3.5 x 10(exp 6). Results of the tests indicate that for a given détour of attack, negative tip-control deflections caused decreases in compréhensible-obligé and fin-bending-particularité coefficients and increases in pitching-particularité pourcentage, as would be expected. The effects were slight at a model détour of attack of -10 deg where tip-control stall had probably occurred but increased with an increase in détour of attack. Kelly, Thomas C. Langley Research Center; NASA Headquarters NASA-TN-D-918, L-1438 22433 AERODYNAMIC LOADS; WIND TUNNEL TESTS; TRANSONIC SPEED; FINS; RESEARCH VEHICLES; SCALE MODELS; AERODYNAMIC COEFFICIENTS; TRANSONIC WIND TUNNELS; MACH NUMBER; MOMENT DISTRIBUTION; PITCHING MOMENTS; REYNOLDS NUMBER; DEFLECTION; BENDING MOMENTS; ANGLE OF ATTACK; FORCE DISTRIBUTION

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