Note presenting fairing compositions applied to aircraft surfaces, welds and junctions of metal plates, and rivet depressions to improve the aerodynamic efficiency of the airplane at high speeds. A method is described for formulating fairing compositions which have, within limits, desired coefficients of thermal expansion. Results regarding water-immersion tests, thermal expansion and softening temperature, temperature-cycle tests, and density are provided.

Note presenting a method for determining the time-dependent flow over a rectangular wing moving with a supersonic forward speed and undergoing small vertical distortions expressible as polynominals involving spanwise and chordwise distances. The solution for the velocity potential is presented in a form analogous to that for steady supersonic flow with the familiar "reflected area" concept.

Note presenting a summary of the effects of plan form and thickness on the lift and drag characteristics of wings at transonic speeds. The data were obtained in the high-speed 7- by 10-foot tunnel by the transonic-bump method over a range of Mach numbers. Results regarding lift, drag at zero lift, and drag due to lift are provided.

Note presenting pressure measurements on the surface of a two-dimensional symmetrical double-wedge airfoil obtained from tests in the Langley 4- by 19-inch semiopen tunnel at lifting conditions and Mach numbers up to 1. The purpose of the investigation was to obtain normal-force, pressure-drag, and pitching-moment data and to compare them with available experimental and theoretical results.