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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Collection: National Advisory Committee for Aeronautics Collection
 Collection: Technical Report Archive and Image Library
Some Recent Contributions to the Study of Transition and Turbulent Boundary Layers

Some Recent Contributions to the Study of Transition and Turbulent Boundary Layers

Date: April 1947
Creator: Dryden, Hugh L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Considerations of the Total Drag of Supersonic Airfoil Sections

Considerations of the Total Drag of Supersonic Airfoil Sections

Date: July 1947
Creator: Ivey, H. Reese & Klunker, E. Bernard
Description: The results of calculations of the viscous and pressure drags of some two-dimensional supersonic airfoils at zero lift are presented. The results indicate that inclusion of viscous drag alters many previous results regarding the desirability of certain airfoil shapes for securing low drags at supersonic speeds. At certain Reynolds and Mach numbers, for instance, a circular-arc airfoil may theoretically have less drag than the previously advocated symmetrical wedge-shape profile; although under different conditions, the circular-arc airfoil may have a higher drag.
Contributing Partner: UNT Libraries Government Documents Department
Tables and Charts of Flow Parameters Across Oblique Shocks

Tables and Charts of Flow Parameters Across Oblique Shocks

Date: August 1948
Creator: Neice, Mary M.
Description: Shock-wave equations have been evaluated for a range of Mach number in front of the shock from 1.05 to 4.0. Mach number behind the shock, pressure ratio, derivation of flow, and angle of shock are presented on charts. Values are also included for density ratio and change in entropy.
Contributing Partner: UNT Libraries Government Documents Department
Two-Dimensional Irrotational Transonic Flows of a Compressible Fluid

Two-Dimensional Irrotational Transonic Flows of a Compressible Fluid

Date: June 1948
Creator: Kuo, Yung-Huai
Description: The methods of NACA TN No. 995 have been slightly modified and extended in include flows with circulation by considering the alteration of the singularities of the incompressible solution due to the presence of the hypergeometric functions in the analytic continuation of the solution. It was found that for finite Mach numbers the only case in which the nature of the singularity can remain unchanged is for a ratio of specific heats equal to -1. From a study of two particular flows it seems that the effect of geometry cannot be neglected, and the conventional "pressure-correction" formulas are not valid, even in the subsonic region if the body is thick, especially if there is a supersonic region in the flow.
Contributing Partner: UNT Libraries Government Documents Department
Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Nitrogen System at Temperatures from 2000 to 5000 Degrees K

Charts for the Computation of Equilibrium Composition of Chemical Reactions in the Carbon-Hydrogen-Nitrogen System at Temperatures from 2000 to 5000 Degrees K

Date: July 1948
Creator: Huff, Vearl N. & Calvert, Clyde S.
Description: Charts are provided for the estimation and progressive adjustment of two independent variables on which the calculations are based. Additional charts are provided for the graphical calculation of the composition.
Contributing Partner: UNT Libraries Government Documents Department
The effect of increased cooling surface on performance of aircraft-engine cylinders as shown by tests of the NACA cylinder

The effect of increased cooling surface on performance of aircraft-engine cylinders as shown by tests of the NACA cylinder

Date: July 1, 1944
Creator: Ellerbrock, Herman H , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculations of economy of 18-cylinder radial aircraft engine with exhaust-gas turbine geared to the crankshaft at cruising speed

Calculations of economy of 18-cylinder radial aircraft engine with exhaust-gas turbine geared to the crankshaft at cruising speed

Date: January 1, 1945
Creator: Zimmerman, Richard H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of exhaust-valve temperatures with engine operating conditions and valve design

Correlation of exhaust-valve temperatures with engine operating conditions and valve design

Date: January 1, 1945
Creator: Sanders, J C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of exhaust-stack shape on the design and performance of the individual cylinder exhaust-gas jet-propulsion system

The effect of exhaust-stack shape on the design and performance of the individual cylinder exhaust-gas jet-propulsion system

Date: November 1, 1942
Creator: Humble, Leroy V
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design of nozzles for the individual cylinder exhaust jet propulsion system

Design of nozzles for the individual cylinder exhaust jet propulsion system

Date: April 1, 1941
Creator: Voss, Fred
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of the 1/8-scale powered model of the Curtiss XBTC-2 airplane I : preliminary investigation of longitudinal stability

Wind-tunnel tests of the 1/8-scale powered model of the Curtiss XBTC-2 airplane I : preliminary investigation of longitudinal stability

Date: June 1, 1944
Creator: Wells, Evalyn G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Compressibility and heating effects on pressure loss and cooling of a baffled cylinder barrel

Compressibility and heating effects on pressure loss and cooling of a baffled cylinder barrel

Date: July 1, 1944
Creator: Ellerbrock, Herman H , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The development and application of high-critical-speed nose inlets

The development and application of high-critical-speed nose inlets

Date: July 1, 1945
Creator: Wright, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Lifting-surface-theory aspect-ratio corrections to the lift and hinge-moment parameters for full-span elevators on horizontal tail surfaces

Lifting-surface-theory aspect-ratio corrections to the lift and hinge-moment parameters for full-span elevators on horizontal tail surfaces

Date: January 1, 1948
Creator: Crandall, Stewart M & Swanson, Robert S
Description: A limited number of lifting-surface-theory solutions for wings with chordwise loadings resulting from angle of attack, parabolic-ac camber, and flap deflection are now available. These solutions were studied with the purpose of determining methods of extrapolating the results in such a way that they could be used to determine lifting-surface-theory values of the aspect-ratio corrections to the lift and hinge-moment parameters for both angle-of-attack and flap-deflection-type loading that could be used to predict the characteristics of horizontal tail surfaces from section data with sufficient accuracy for engineering purposes. Such a method was devised for horizontal tail surfaces with full-span elevators. In spite of the fact that the theory involved is rather complex, the method is simple to apply and may be applied without any knowledge of lifting-surface theory. A comparison of experimental finite-span and section value and of the estimated values of the lift and hinge-moment parameters for three horizontal tail surfaces was made to provide an experimental verification of the method suggested. (author).
Contributing Partner: UNT Libraries Government Documents Department
A theoretical investigation of the lateral oscillations of an airplane with free rudder with special reference to the effect of friction

A theoretical investigation of the lateral oscillations of an airplane with free rudder with special reference to the effect of friction

Date: March 1, 1943
Creator: Sternfield, Leonard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air-consumption parameters for automatic mixture control of aircraft engines

Air-consumption parameters for automatic mixture control of aircraft engines

Date: September 1, 1944
Creator: Shames, Sidney J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel

Comparison of Vee-Type and Conventional Tail Surfaces in Combination with Fuselage and Wing in the Variable-Density Tunnel

Date: July 1, 1941
Creator: Greenberg, Harry
Description: The pitching and the yawing moments of a vee-type and a conventional type of tail surface were measured. The tests were made in the presence of a fuselage and a wing-fuselage combination in such a way as to determine the moments contributed by the tail surfaces. The results showed that the vee-type tail tested, with a dihedral angle of 35.3 deg, was about 71 percent as effective in pitch as the conventional tail and had a yawing-moment to pitching-moment ratio of 0.3. The conventional tail, the panels of which were all congruent to those of the vee-type tail, had a yawing-moment to pitching-moment ratio of 0.48. These ratios are in fair agreement with values calculated by methods shown in this and previous reports. The values of the measured moments were reduced from 15 to 25 percent of the calculated value by fuselage interference.
Contributing Partner: UNT Libraries Government Documents Department
Experiments on drag of revolving disks, cylinders and streamline rods at high speeds

Experiments on drag of revolving disks, cylinders and streamline rods at high speeds

Date: June 1, 1944
Creator: Regier, Arthur
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The use of geared spring tabs for elevator control

The use of geared spring tabs for elevator control

Date: February 1, 1945
Creator: Phillips, William H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of altitude on cooling

The effect of altitude on cooling

Date: March 1, 1943
Creator: Wood, George P
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight Tests of Modifications to Improve the Aileron Control Characteristics of a North American XP-51 Airplane (AC No. 41-38)

Flight Tests of Modifications to Improve the Aileron Control Characteristics of a North American XP-51 Airplane (AC No. 41-38)

Date: June 1, 1942
Creator: Hoover, Herbert H.
Description: Investigations were undertaken to improve the ailerons of a P-51 fighter so as to obtain greater effectiveness without increasing the stick forces. Modifications consisted of increasing the deflection range of the aileron to 70 percent and changing the original concave section to a thick section with beveled trailing edge. Results of the modified ailerons showed an increase in effectiveness over the original aileron of 70 percent at low speed and 55 percent at high speeds.
Contributing Partner: UNT Libraries Government Documents Department
Application of spring tabs to elevator controls

Application of spring tabs to elevator controls

Date: October 1, 1944
Creator: Phillips, William H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic heating and the deflection of drops by an obstacle in an air stream in relation to aircraft icing

Aerodynamic heating and the deflection of drops by an obstacle in an air stream in relation to aircraft icing

Date: October 1, 1940
Creator: Kantrowitz, Arthur
Description: Two topics of interest to persons attempting to apply the heat method of preventing ice formation on aircraft are considered. Surfaces moving through air at high speed are shown, both theoretically and experimentally, to be subject to important aerodynamic heating effects that will materially reduce the heat required to prevent ice. Numerical calculations of the path of water drops in an air stream around a circular cylinder are given. From these calculations, information is obtained on the percentage of the swept area cleared of drops.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Date: September 1, 1942
Creator: Baals, Donald D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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