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20 per cent absolute coefficient accur Aeronautics angle of attack approximately aspect ratio attack for different burble calibrations cent c flap cent chord flap Chief coefficient versus angle coefficient versus flap Committee for Aeronautics Constant corresponding curves Daniel Guggenheim Density Wind Tunnel determine different flap angles distribution of pressure Eastman effect errors experimental Figure flap displacement force coefficient versus given higher hinge increase indicate integrated Langley larger length lift load located manometer maximum normal force mean measured ment moments National Advisory Committee Navy negative normal force coefficient obtained orifice parameters particularly pitching plotted position pressure distribution record Reference Reynolds Number 0.356X10 scale setting show the effect showing the distribution shown slope smaller Standard surface SYMMETRICAL AIRFOIL tests theoretical theory trailing edge flaps values Variable Density Wind Washington weight wing
Page 7 - Higgins, George J., and Jacobs, Eastman N.: The Effect of a Flap and Ailerons on the NACA-M 6 Airfoil Section.
Page 7 - Smith, RH: Lift, Drag, and Elevator Hinge Moments of Handley-Page Control Surfaces.
Page 7 - 5. The effect of flaps should be further investigated at large values of the Reynolds Number to find the effect of different types of hinges and fairings at the hinge, including also slots between the airfoil and
Page 6 - 3. The pitching moments and hinge moments obtained from these tests agree very well with the theoretical results for small flap displacements, regardless of the size of the flap.
Page 6 - 4. For flaps 20 per cent of the chord or smaller the theory does not give a good measure of the actual flap effect