Finite Difference Calculations of the NACA 64A-410Airfoil Oscillating Sinusoidally in Pitch at M sub Infinity = 0.72.

摘要

A finite difference procedure based upon the exact unsteady inviscid adiabatic flow equations is used to calculate the flow over a NACA 64A-410airfoil oscillating sinusoidally in pitch at M sub infinity = 0.72. At the reduced frequencies k = 0.2and 1.0the amplitude of the pitch is 2degrees about the mean incidence of 2degrees,while at the reduced frequency k = 5.0,the amplitude is reduced to 0.4degrees. (The airfoil chord is used in defining k.) The resulting unsteady chordwise pressure distributions,and the time variations of CL and CM,all in the periodic stage,are given for the three values of k. (Author)