The total drag coefficients of 60° cone cylinders of fineness ratio 2.07 were measured in free flight at Mach numbers from 1.5 to 8.2. Drag measurements also were made for 30° and 90° cone cylinders with fineness ratios of 3.07 and 1-70, respectively, at Mach numbers between 1.5 and 3.5. The Reynolds numbers based on model length were between 0.3 and 2.4 million.nIt was concluded that the Taylor and McColl theory for the wave drag of cones is accurate for the 60° cone over the entire range of Mach numbers from 2 to 8. (No imperfect gas effects were encountered in these tests.) In the narrow range of Mach numbers greater than that of wave detachment but less than that for which the flow is everywhere supersonic, the Taylor and McColl theory for the wave drag of the 9°° cone was found to be subject to question. The variation with Mach number of the base drag of the 60° cone cylinder was estimated from the total drag measurements at Mach numbers between 2 and 4.5.
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