ROTOR/WING SERIES VI WIND TUNNEL TEST 7-FOOT DIAMETER MODEL IN THE NASA LRC 30-BY-60-FOOT WIND TUNNEL
HUGHES TOOL CO CULVER CITY CA AIRCRAFT DIV
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Wind tunnel tests of a rotorwing model were conducted for three purposes To compare the results of testing the same model in a small and a large wind tunnel to investigate rotorwing planform effects on performance and flying qualities to investigate in detail the low rotor speed range of conversion. The data gathered from testing the 7-foot diameter model in the 8- by-10-foot tunnel and in the 30-by-60-foot tunnel were in good agreement for rotor advance ratios greater than 0.15.