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 Decade: 1930-1939
 Serial/Series Title: NACA Technical Memorandums
 Collection: Technical Report Archive and Image Library
The 5- by 7-meter wind tunnel of the DVL

The 5- by 7-meter wind tunnel of the DVL

Date: March 1, 1936
Creator: Kramer, M
Description: The report contains a description of the DVL wind tunnel. According to the cones fixed, an elliptical stream with axes 5 by 7 meters and length 9 meters, or a stream 6 by 8 meters in cross section and 11 meters in length is available. The top speed with the smaller cone is 65 meters per second. The testing equipment consists of an automatic six-component balance and a test rig for propellers and engines up to 650 horsepower.
Contributing Partner: UNT Libraries Government Documents Department
The 1929 Rhon soaring-flight contest

The 1929 Rhon soaring-flight contest

Date: April 1, 1930
Creator: Lippisch, Alexander
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.
Contributing Partner: UNT Libraries Government Documents Department
The 1933 contest for the Deutsch de la Meurthe trophy

The 1933 contest for the Deutsch de la Meurthe trophy

Date: October 1, 1933
Creator: Leglise, Pierre
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The 1934 contest for the Deutsch de la Meurthe trophy

The 1934 contest for the Deutsch de la Meurthe trophy

Date: February 1, 1935
Creator: Leglise, Pierre
Description: This report presents a description of the rules, history and new technical innovations in the Deutsch de la Meurthe Cup race of 1934.
Contributing Partner: UNT Libraries Government Documents Department
The Aachen wind-tunnel balance

The Aachen wind-tunnel balance

Date: November 1, 1934
Creator: Wieselsberger, C
Description: A description of the balance in the Aachen wind-tunnel.
Contributing Partner: UNT Libraries Government Documents Department
Accurate calculation of multispar cantilever and semicantilever wings with parallel webs under direct and indirect loading

Accurate calculation of multispar cantilever and semicantilever wings with parallel webs under direct and indirect loading

Date: March 1, 1932
Creator: Sanger, Eugen
Description: In the present report the computation is actually carried through for the case of parallel spars of equal resistance in bending without direct loading, including plotting of the influence lines; for other cases the method of calculation is explained. The development of large size airplanes can be speeded up by accurate methods of calculation such as this.
Contributing Partner: UNT Libraries Government Documents Department
Activation of hydrocarbons and the octane number

Activation of hydrocarbons and the octane number

Date: October 1, 1939
Creator: Peschard, Marcel
Description: This report presents an examination of the history of research on engine knocking and the various types of fuels used in the investigations of this phenomenon. According to this report, the spontaneous ignition of hydrocarbons doped with oxygen follows the logarithmic law within a certain temperature range, but not above 920 degrees K. Having extended the scope of investigations to prove hydrocarbons, the curves of the mixtures burned by air should then be established by progressive replacement of pure iso-octane with heptane. Pentane was also examined in this report.
Contributing Partner: UNT Libraries Government Documents Department
Additional test data on static longitudinal stability

Additional test data on static longitudinal stability

Date: August 1, 1934
Creator: Hubner, Walter
Description: The purpose of this investigation was to explore the influence of weights of the controls on the stability with elevator released. The available test data were extended to stability with elevator locked. In this connection the study of the propeller effect seemed of vital importance.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic aspect of wing-fuselage fillets

The aerodynamic aspect of wing-fuselage fillets

Date: February 1, 1935
Creator: Muttray, H
Description: Model tests prove the feasibility of enhancing the aerodynamic qualities of wing-fuselage fillets by appropriate design of fuselage and wing roots. Abrupt changes from maximum fuselage height to wing chord must be avoided and every longitudinal section of fuselage and wing roots must be so faired and arranged as to preserve the original lift distribution of the continuous wing. Adapting the fuselage to the curvilinear circulation of the wing affords further improvement. The polars of such arrangements are almost the same as those of the "wing alone," thus voiding the superiority of the high-wing type airplane known with conventional design.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic forces and moments of a seaplane on the water

Aerodynamic forces and moments of a seaplane on the water

Date: November 1, 1933
Creator: Kohler, M
Description: This report gives the results of wind-tunnel tests with a seaplane model as a contribution to the solution of the aerodynamic problems. In the tests it was assumed that the seaplane rested motionless on the water and was exposed, in various positions with respect to the supposedly flat surface of the water, to a uniform air current 0 to 360 degrees.
Contributing Partner: UNT Libraries Government Documents Department
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