SOLUTION OF THE LANE-FRIEDMAN INTEGRAL EQUATION.

The solution of the Lane-Friedman upwash integral equation is completed, which gives partly new numerical techniques for computing force and moment coefficients for the following structures: 1) airfoils oscillating in a given manner in a staggered cascade, 2) a single wing oscillating harmonically between two parallel walls, and 3) a single wing oscillating harmonically in freestream. A common method for computing the critical flutter speed of these structures is given. The computation of critical flutter speed is based on the assumption of coupled flexural-torsion oscillation of the blades. This paper presents, therefore, a method for investigating the most general flutter phenomenon which can occur at low incidence.