Annual Report of the National Advisory Committee for Aeronautics, 612–644 leidimaiU.S. Government Printing Office, 1939 Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37. |
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28 Angle aerodynamic center ahead of c/4 ailerons air speed air-fuel ratio aircraft airfoil section airplane angle at 0.75R Angle of attack attack for infinite beam Blade angle c.p. in percent calculated characteristics chord from forward chromium-molybdenum steel Civil Aeronautics Authority Clark Cmac coef column combustion compressibility Corrected for tunnel-wall Corrected to infinite cylinder determined diameter Drag coefficient duralumin efficiency end of chord engine speed equation Fairchild 22 flight forward end Fowler flap fuel given increase indicated infinite aspect ratio investigation LANGLEY FIELD Lift coefficient lift to drag load main airfoil maximum lift method Normal-force coefficient obtained Percent of chord pitching moment plain flap Profile-drag coefficient radial engine Ratio of lift reference root chord shown in figure span stall stress surface take-off temperature tests thickness thrust tion tip speeds torque tubes tunnel-wall effect V/nD values velocity wind tunnel yawing yield strength
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