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 Decade: 1940-1949
 Collection: National Advisory Committee for Aeronautics Collection
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