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 Decade: 1940-1949
 Serial/Series Title: NACA Technical Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
Supplement to Comparison of automatic control systems

Supplement to Comparison of automatic control systems

Date: August 1, 1941
Creator: Oppelt, W
Description: This analysis deals with the indirect regulator, wherefrom the behavior of the direct regulator is deduced as a limiting case. The prime mover is looked upon as "independent of the load": a change in the adjusting power (to be applied) for the control link (as, for example, in relation to the adjusting path (eta) with pressure valves or the rudder of vessels) does not modify the actions of the prime mover. Mass forces and friction are discounted; "clearance" also is discounted in the transmission links of the regulator.
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Investigations on the stability, oscillation, and stress conditions of airplanes with tab control.  Second partial report : application of the solutions  obtained in the first partial report to tab-controlled airplanes.

Investigations on the stability, oscillation, and stress conditions of airplanes with tab control. Second partial report : application of the solutions obtained in the first partial report to tab-controlled airplanes.

Date: September 1, 1949
Creator: Filzek, B
Description: The first partial report, FB 2000, contained a discussion of the derivation of the equations of motion and their solutions for a tab-controlled airplane; the results obtained there are now to be applied to the longitudinal motion of tab-controlled airplanes. In view of the abundance of structural factors and aerodynamic parameters, a general discussion of the problems is unfeasible. Thus it is demonstrated on the basis of examples what stability, oscillation, and stress conditions are to be expected for tab-controlled airplanes. (author).
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On laminar and turbulent friction

On laminar and turbulent friction

Date: September 1, 1946
Creator: Von Karman, TH
Description: Report deals, first with the theory of the laminar friction flow, where the basic concepts of Prandtl's boundary layer theory are represented from mathematical and physical points of view, and a method is indicated by means of which even more complicated cases can be treated with simple mathematical means, at least approximately. An attempt is also made to secure a basis for the computation of the turbulent friction by means of formulas through which the empirical laws of the turbulent pipe resistance can be applied to other problems on friction drag. (author).
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A Ram-Jet Engine for Fighters

A Ram-Jet Engine for Fighters

Date: October 1, 1947
Creator: Sanger, E
Description: Simple and accurate calculations are made of the flow process in a continuous compressorless Lorin jet-propulsion unit. Experimental confirmation is given from towing tests on an airplane at flying speeds up to 200 miles per second. An analysis is made of the performance of a fighter-type airplane designed for utilization of this propulsion system.
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Force and pressure-distribution measurements on a rectangular wing with a slotted droop nose and with either plain and split flaps in combination or a slotted flap.

Force and pressure-distribution measurements on a rectangular wing with a slotted droop nose and with either plain and split flaps in combination or a slotted flap.

Date: March 1, 1947
Creator: Lemme, H G
Description: Force measurements and pressure distribution measurements on the midsection were made on a rectangular wing with slotted droop nose and end plates, on which could be placed a choice of either a plain flap-split flap combination or a slotted flap. (author).
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Airfoil measurements in the DVL high-speed wind tunnel (2.7-meter diameter)

Airfoil measurements in the DVL high-speed wind tunnel (2.7-meter diameter)

Date: June 1, 1949
Creator: Gothert, B
Description: Report is a brief summary of investigations on symmetrical and cambered airfoils in the DVL high-speed tunnel. Some information on the effects of low aspect ratio are also included.
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Method of characteristics for three-dimensional axially symmetrical supersonic flows.

Method of characteristics for three-dimensional axially symmetrical supersonic flows.

Date: January 1, 1947
Creator: Sauer, R
Description: An approximation method for three-dimensional axially symmetrical supersonic flows is developed; it is based on the characteristics theory (represented partly graphically, partly analytically). Thereafter this method is applied to the construction of rotationally symmetrical nozzles. (author).
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of the Fuselage

Aerodynamics of the Fuselage

Date: December 1, 1942
Creator: Multhopp, H.
Description: The present report deals with a number of problems, particularly with the interaction of the fuselage with the wing and tail, on the basis of simple calculating method's derived from greatly idealized concepts. For the fuselage alone it affords, in variance with potential theory, a certain frictional lift in yawed flow, which, similar to the lift of a wing of small aspect ratio, is no longer linearly related to the angle of attack. Nevertheless there exists for this frictional lift something like a neutral stability point the position of which on oblong fuselages appears to be associated with the lift increase of the fuselage in proximity to the zero lift, according to the present experiments. The Pitching moments of the fuselage can be determined with comparatively great reliability so far as the flow conditions in the neighborhood of the axis of the fuselage can be approximated if the fuselage were absent, which, in general, is not very difficult. For the unstable contribution of the fuselage to the static longitudinal stability of the airplane it affords comparatively simple formulas, the evaluation of which offers little difficulty. On the engine nacelles there is, in addition a very substantial wing moment contribution induced ...
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Possibilities of Reducing the Length of Axial Superchargers for Aircraft Motors

Possibilities of Reducing the Length of Axial Superchargers for Aircraft Motors

Date: January 1, 1947
Creator: Eckert, B.
Description: Axial blowers are gaining importance as aircraft engine superchargers. However, the pressure head obtainable per stage is small. Due to the necessary great number of stages, the physical length of the blower becomes too great for an airworthy device. This report discusses several types of construction that permit a reduction in the length of the blower.
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Thermal Theory of Combustion and Explosion, 3, Theory of Normal Flame Propagation

Thermal Theory of Combustion and Explosion, 3, Theory of Normal Flame Propagation

Date: September 1, 1942
Creator: Semenov, N. N.
Description: The technical memorandum covers experimental data on flame propagation, the velocity of flame propagation, analysis of the old theoretical views of flame propagation, confirmation of the theory for simple reactions (theory of combustion of explosive substances and in particular nitroglycol), and check of the theory by example of a chain oxidizing reaction (theory of flame propagation in carbon monoxide, air and carbon monoxide - oxygen mixtures).
Contributing Partner: UNT Libraries Government Documents Department
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