The free flight technique (C4/was extended to low density flows to measure sphere drag at approximately Mach 15 over a free stream Knudsen number range of .0027 to .25. Comparison of the data obtained with those of other investigators indicates that: 7he free flight technique is useful for shock tunnel measurements of aerodynamic forces in non-continuum flows., '-b) There is little to choose from betweena, a correlating variable for experimental sphere drag coefficients. c) 6 The parameter"'CD-GD? ields a useful correlation of sphere drag over a wide ra g.-gya.numbers, Reynolds number and wall Temperatures.-7 =7.
The geometrical equivalence isAgain, placing {F} in terms of {h} by combining Eqs. (9)-(ll) and identifying the result with Eq.(2) yields the oscillatory strip AIC matrix.[In the absence of the control surface, this reduces toOnce the AIC partitions are obtained for each strip, the total AIC matrix is formed as in Eq.(3).i~\ VL h L a 1 i" 1 0
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