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absolute coefficient additional airfoil set-up airfoil tests alignment angle of attack axis balance basis center of pressure circular jet circular side Jet Cl Cm Clark Y airfoil cones correction factors corresponding curves decrease derived determined dimensions direction distribution drag coefficient dynamic pressure effect entrance cone Equation experimental flow force tests four jets free air conditions greater horizontal inches increase jet boundaries JET BOUNDARY CORRECTIONS length lift lift wires maximum lift mean measured necessary normal Note obtained pitching moments plotted position pressure variation proper ratio of model rectangular Jet Reference relative represent respectively Reynolds Number setting shapes shown in Figure span Standard static pressure stream SYMBOLS Table taken theoretical three airfoils tion turbulence United values various jets versus Washington weight wind tunnel wing wires zero lift
Page 22 - Glauert, H.: The Effect of the Static Pressure Gradient on the Drag of a Body Tested in a Wind Tunnel.
Page 22 - Wieselsberger, C.: Wind Tunnel Tests of Correction Formula for wings of Large Span.
Page 3 - the purpose of obtaining a method of correcting to free air conditions the results of airfoil force tests in