You limited your search to:

 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.
Contributing Partner: UNT Libraries Government Documents Department
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
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).
Contributing Partner: UNT Libraries Government Documents Department
A Ram-Jet Engine for Fighters

A Ram-Jet Engine for Fighters

Date: October 1, 1947
Creator: Sanger, E & Bredt, I
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.
Contributing Partner: UNT Libraries Government Documents Department
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).
Contributing Partner: UNT Libraries Government Documents Department
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).
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of the Behavior of Thin-Walled Panels with Cutouts

Investigation of the Behavior of Thin-Walled Panels with Cutouts

Date: September 1, 1946
Creator: Podorozhny, A. A.
Description: The present paper deals with the computation and methods of reinforcement of stiffened panels with cutouts under bending loads such as are applied to the sides of a fuselage. A comparison is maade between the computed and test results. Results are presented of tests on panels with cutouts under tensile and compressive loads.
Contributing Partner: UNT Libraries Government Documents Department
Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed

Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed

Date: January 1, 1947
Creator: Ackeret, J.; Feldmann, F. & Rott, N.
Description: The mutual influences of compression shocks and friction boundary layers were investigated by means of high speed wind tunnels.Schlieren optics provided a clear picture of the flow phenomena and were used for determining the location of the compression shocks, measurement of shock angles, and also for Mach angles. Pressure measurement and humidity measurements were also taken into consideration.Results along with a mathematical model are described.
Contributing Partner: UNT Libraries Government Documents Department
The Calculation of Compressible Flows with Local Regions of Supersonic Velocity

The Calculation of Compressible Flows with Local Regions of Supersonic Velocity

Date: March 1, 1947
Creator: Goethert, B. & Kawalki, K. H.
Description: This report addresses a method for the approximate calculation of compressible flows about profiles with local regions of supersonic velocity. The flow around a slender profile is treated as an example.
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST