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 Decade: 1940-1949
 Year: 1943
 Month: April
 Collection: National Advisory Committee for Aeronautics Collection
Effect of varying percentages of exhaust gas on engine performance

Effect of varying percentages of exhaust gas on engine performance

Date: April 1, 1943
Creator: Barnett, Henry C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of wing leading-edge slots on the spin and recovery characteristics of airplanes

Effect of wing leading-edge slots on the spin and recovery characteristics of airplanes

Date: April 1, 1943
Creator: Pitkin, Marvin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of a typical nacelle on the characteristics of a thick low-drag airfoil critically affected by leading-edge roughness

Effects of a typical nacelle on the characteristics of a thick low-drag airfoil critically affected by leading-edge roughness

Date: April 1, 1943
Creator: Ellis, Macon C , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Investigation of a Model of a Two-Stage Turboblower

Experimental Investigation of a Model of a Two-Stage Turboblower

Date: April 1, 1943
Creator: Dovjik, s.
Description: In the present paper an investigation is made of two stages of a multistage turboblower having a vaneless diffuser behind the impeller and guide vanes at the inlet to the nest stage. The method employed was that of investigating the performance of the successive elements of the blower (the impeller, vaneless diffuser, ets.) whereby the kinematics of the flow through the blower could be followed and the pressure at the different points computed. The character of the flow and the physical significance of the loss coefficients could thereby be determined so as to secure the best agreement of the computed with the actual performance of the blower. Since the tests were carried out for various delivery volumes, the dependence of the coefficients on a number of factors (angle of attack, velocities, etc.) could be obtained. The distribution of the losses that occur during the transformation of dynamic pressure at the impeller exit into static pressure could be found and likewise the range within which the friction coefficient varies in the vaneless diffuser. With the aid of factors having a certain physical significance, the centrifugal blower could be computed on the basis of a more or less schematical consideration of the ...
Contributing Partner: UNT Libraries Government Documents Department
Flight tests of a glider model towed by twin parallel towlines

Flight tests of a glider model towed by twin parallel towlines

Date: April 1, 1943
Creator: Mckinney, Marion O , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flying qualities and stalling characteristics of North American XP-51 airplane

Flying qualities and stalling characteristics of North American XP-51 airplane

Date: April 1, 1943
Creator: Garris, Howard W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight-tunnel investigation of the effect of the fuselage length and the aspect ratio and size of the vertical tail on lateral stability and control

Free-flight-tunnel investigation of the effect of the fuselage length and the aspect ratio and size of the vertical tail on lateral stability and control

Date: April 1, 1943
Creator: Draper, John W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Heat Transfer of Airfoils and Plates

Heat Transfer of Airfoils and Plates

Date: April 1, 1943
Creator: Seibert, Otto
Description: The few available test data on the heat dissipation of wholly or partly heated airfoil models are compared with the corresponding data for the flat plate as obtained by an extension of Prandtl's momentum theory, with differentiation between laminar and turbulent boundary layer and transitional region between both, the extent and appearance of which depend upon certain critical factors. The satisfactory agreement obtained justifies far-reaching conclusions in respect to other profile forms and arrangements of heated surface areas. The temperature relationship of the material quantities in its effect on the heat dissipation is discussed as far as is possible at tk.e present state of research, and it is shown that the profile drag of heated wing surfaces can increase or decrease with the temperature increase depending upon the momentarily existent structure of the boundary layer.
Contributing Partner: UNT Libraries Government Documents Department
An investigation of aircraft heaters XI : measured and predicted performance of a slotted-fin exhaust gas and air heat exchanger

An investigation of aircraft heaters XI : measured and predicted performance of a slotted-fin exhaust gas and air heat exchanger

Date: April 1, 1943
Creator: Morrin, E H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An investigation of the air flow around a Martin PBM-3 flying boat by means of tufts

An investigation of the air flow around a Martin PBM-3 flying boat by means of tufts

Date: April 1, 1943
Creator: Ebert, John W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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