Note presenting a consideration of the effect on engine performance of a known inequality of distribution. A measure of perfect distribution is provided and some of the factors that influence the unequal distribution of power among cylinders.

"The strength and reliability of airplanes depend greatly on the careful design and manufacture of fittings, couplings, and other highly stressed parts. The more important parts of the airplane must be occasionally tested for increased loads and in order to avoid the possibility of defects creeping in during subsequent production. Strength tests are discussed for fittings for wing spar joints, fittings for strut connections, internal bracing, control gear, and landing gear" (p. 1).

In this paper the application of the slip curve method to the design and analysis of windmills is discussed and illustrated by example.

Note presenting a graphic method for calculating the speed and climbing ability of airplanes. This method starts from the actual power developed by the engine and makes it possible to determine all factors which together constitute what are known as flight performances for any combination of engine and airplane from the single graphic diagram given.

The equilibrium, in still air, of a "stationary" helicopter (i.e., of one having neither vertical nor translational velocity, but a tendency to remain practically motionless within restricted limits of space) presents some difficulty in practice and justifies a theoretical investigation of its "inherent stability," i.e., independent of the pilot.

Report presenting a description of a parachute design contest. The object of this contest was to obtain a parachute of light weight and small bulk, suitable for airplanes. The primary areas of focus were safety, ability to be installed on airplanes, speed, materials, and behavior of the parachutes in the air.

This paper constitutes a general theoretical discussion of the damping factor in roll, together with the results of wind tunnel tests on the continuous rolling of U.S.A. 30 airfoil.

Methods for shortening the landing run are discussed as well as the need for more emergency landing fields that will, by necessity, have to be short fields.

This report endeavors to show the possibility of determining the rate of acceleration and the advantage of having such an accelerometer in addition to other aviation instruments. Most of the discussions concern balloons.