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The 1929 Rhon soaring-flight contest

Description: The limitation of the 1929 contest to performance gliders necessitated the establishment of a formula which would make it possible to distinguish between performance gliders and school and training gliders. The sinking speed was therefore adopted as the basis for such a distinction, and the requirement was made that the sinking speed of a performance glider should not exceed 0.8 m/s. The rest of the report details the different entries with regard to design and performance.
Date: April 1930
Creator: Lippisch, Alexander
Item Type: Refine your search to only Report
open access

Experimental determination of jet boundary corrections for airfoil tests in four open wind tunnel jets of different shapes

Description: "This experimental investigation was conducted primarily for the purpose of obtaining a method of correcting to free air conditions the results of airfoil force tests in four open wind tunnel jets of different shapes. Tests were also made to determine whether the jet boundaries had any appreciable effect on the pitching moments of a complete airplane model. Satisfactory corrections for the effect of the boundaries of the various jets were obtained for all the airfoils tested, the span of the la… more
Date: April 16, 1930
Creator: Knight, Montgomery & Harris, Thomas A.
Item Type: Refine your search to only Report
open access

Experimental Investigation of Aircraft Propellers Exposed to Oblique Air Currents

Description: "Two screw propellers, a normal airplane propeller with a pitch/diameter ratio H/D = 0.5 and a helicopter propeller H/D = 0.2 were tested in the large wind tunnel of the Gottigen Aerodynamic Institute. With both propellers the angle between the propeller axis and the direction of the wind was varied from 0 to 90 degrees. In addition to the three force and the three moment components in a wind-fast coordinate system, the corresponding components in a propeller-fast coordinate system, a total of … more
Date: April 1930
Creator: Flachsbart, O. & Kröber, G.
Item Type: Refine your search to only Report
open access

Improving the Performance of Multi-Engined Airplanes by Means of Idling Propellers: The "Free-Wheel" Propeller

Description: In order to demonstrate the importance of free-wheeling propellers, this report considers the braking effect of a propeller on a stopped engine when the propeller is rigidly connected with the engine shaft and also when mounted on a free-wheel hub. The cases of propellers of asymmetric and symmetric section are discussed. The author describes the mechanism of the free-wheel propeller as constructed for this test. The results obtained with the device mounted on a 1,000 horsepower two-engine airp… more
Date: April 1930
Creator: Pillard, M.
Item Type: Refine your search to only Report
open access

An Investigation of the Effectiveness of Ignition Sparks

Description: "The effectiveness of ignition sparks was determined by measuring the volume (or mass) of hydrogen and of oxygen which combines at low pressures. The sparks were generated by a magneto and an ignition spark coil. It was found that with constant energy the amount of reaction increases as the capacitance component of the spark increases" (p. 575).
Date: April 1930
Creator: Peters, Melville F.; Summerville, Wayne L. & Davis, Merlin
Item Type: Refine your search to only Report
open access

Pressure distribution on the tail surfaces of a PW-9 pursuit airplane in flight

Description: Presented here are pressure distribution data obtained from the tail surfaces of a PW-9 in a number of flight maneuvers. The results given are part of those obtained in an extensive investigation of the pressure distribution over all of the lifting and control surfaces of this airplane. The results are given in tabular and curve form and are discussed briefly with respect to their comparison with existing tail surface design specifications. It is recommended that tail load design loadings shoul… more
Date: April 1930
Creator: Rhode, Richard V.
Item Type: Refine your search to only Report
open access

Pressure distribution over a symmetrical airfoil section with trailing edge flap

Description: "Measurements were made to determine the distribution of pressure over one section of an R. A. F. 30 (symmetrical) airfoil with trailing edge flaps. In order to study the effect of scale measurements were made with air densities of approximately 1 and 20 atmospheres. Isometric diagrams of pressure distribution are given to show the effect of change in incidence, flap displacement, and scale upon the distribution. Plots of normal force coefficient versus angle of attack for different flap displa… more
Date: April 2, 1930
Creator: Jacobs, Eastman N. & Pinkerton, Robert M.
Item Type: Refine your search to only Report
open access

Ratier Metal Propeller With Pitch Variable in Flight

Description: One of the serious sources of difficulties in variable pitch propellers is the turning moment or torque due to the centrifugal force which tends to bring the mean plane of the blades into the plane of rotation. This moment, which is found elsewhere only in propellers with removable blades, is so great that the aerodynamic forces, as regards their effect on the torsion, become entirely negligible in comparison with it. This report presents the Ratier Company's solution to changing the pitch of a… more
Date: April 1930
Creator: Léglise, Pierre
Item Type: Refine your search to only Report
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