Aerodynamic Coefficients for an Oscillating Airfoil With Hinged Flap, With Tables for a Mach Number of 0.7.

摘要

Dietze's method for the solution of Possio's integral equation has been used to determine the chordwise distribution of lift on an oscillating airfoil with simple hinged flap in two-dimensional compressible flow (subsonic). The results of these calculations have been used to prepare tables of aerodynamic coefficients for lift, pitching moment (referred to quarter-chord point), and flap hinge moment for a Mach number of 0.7; the motions considered are vertical translation, airfoil rotation about the quarter-chord point, and rotation of the flap about its hinge line. Aerodynamic coefficients are tabulated for values of TR (ratio of flap chord to total chord) and for 12 values of reduced frequency dielectric flux, covering the range from 0 to 0.7. Results are given for one value of Mach number, M = 0.7. Data of this kind have already been presented by Dietze for one value of the ratio of flap chord to total chord, TR = 0.l5; these results have been checked independently, and calculations have been carried out for three additional values, TR -0.24, 0.33, and 0.42 Certain auxiliary parameters, which will be needed in any further calculations of this type, are presented for future reference.