Gottingen six-component scale measurements on a Junkers A 35 airplane model

The suggestion for the measurements collected in this report was prompted by the results of spinning experiments. For the theoretical spinning investigations there was a lack of data on lateral force, yawing, and rolling moment of airplanes

Flight tests for the determination of static longitudinal stability

The accuracy of the instruments used for flight test measurements has been inadequate so a new series of tests were commissioned with the development of an accurate elevator setting recorder

Hermann Schlichting: Nachruf

Vorgetragen in der Plenarversammlung am 6.4.198

The German Investigation of the Accident at Meopham (England)

This report is a recounting of the German investigation of the crash of a commercial Junkers F 13 ge in England. The English report is examined and compared with the German interpretation of the accident

Modellversuche über den Winddruck auf ein Haus ohne und mit Windschutz

The wind pressures on a building can be decreased by a shelter hedge. Windtunnel experiments show how this shelter effect depends from the distance between hedge and house and from the wind direction

NACA Technical Memorandums

"In Prandtl's airfoil theory the monoplane was replaced by a single lifting vortex line and yielded fairly practical results. However, the theory remained restricted to the straight wing. Yawed wings and those curved in flight direction could not be computed with this first approximation; for these the chordwise lift distribution must be taken into consideration. For the two-dimensional problem the transition from the lifting line to the lifting surface has been explained by Birnbaum. In the present report the transition to the three-dimensional problem is undertaken" (p. 1)

Über die Sortierung durch Luftkräfte

The same differential equations are valid for all apparatus in which the weight and the air forces due to the relative motion of grain and air are used in the sorting process. The velocity of sinking is found to be the only determining factor. The advantages and disadvantages of the different apparatus are discussed and a new method for testing their aerodynamic quality is suggested

NACA Technical Memorandums

The accuracy of the instruments used for flight test measurements has been inadequate so a new series of tests were commissioned with the development of an accurate elevator setting recorder

NACA Technical Memorandums

The suggestion for the measurements collected in this report was prompted by the results of spinning experiments. For the theoretical spinning investigations there was a lack of data on lateral force, yawing, and rolling moment of airplanes

The Monoplane as a Lifting Vortex Surface

In Prandtl's airfoil theory the monoplane was replaced by a single lifting vortex line and yielded fairly practical results. However, the theory remained restricted to the straight wing. Yawed wings and those curved in flight direction could not be computed with this first approximation; for these the chordwise lift distribution must be taken into consideration. For the two-dimensional problem the transition from the lifting line to the lifting surface has been explained by Birnbaum. In the present report the transition to the three-dimensional problem is undertaken. The first fundamental problem involves the prediction of flow, profile, and drag for prescribed circulation distribution on the straight rectangular wing, the yawed wing for lateral boundaries parallel to the direction of flight, the swept-back wing, and the rectangular wing in slipping, with the necessary series developments for carrying through the calculations, the practical range of convergence of which does not comprise the wing tips or the break point of the swept-back wing. The second problem concerns the calculation of the circulation distribution with given profile for a slipping rectangular monoplane with flat profile and aspect ratio 6, and a rectangular wing with cambered profile and variable aspect ratio-the latter serving as check of the so-called conversion formulas of the airfoil theory