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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Serial/Series Title: NACA Technical Notes
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
The calculation of span LCAD distributions of swept-back wings

The calculation of span LCAD distributions of swept-back wings

Date: December 1, 1941
Creator: Mutterperl, William
Description: Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for sweep-back angles of 0 degrees, 30 degrees, and 45 degrees, and for aspect ratios of 3, 6, and 9. Some comments on the stalling of swept-back wings are included.
Contributing Partner: UNT Libraries Government Documents Department
Spin tests of two models of a low-wing monoplane to investigate scale effect in the model test range

Spin tests of two models of a low-wing monoplane to investigate scale effect in the model test range

Date: May 1, 1941
Creator: Donlan, Charles C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Methods of analyzing wind-tunnel data for dynamic flight conditions

Methods of analyzing wind-tunnel data for dynamic flight conditions

Date: October 1, 1941
Creator: Donlan, C J & Recant, I G
Description: The effects of power on the stability and the control characteristics of an airplane are discussed and methods of analysis are given for evaluating certain dynamic characteristics of the airplane that are not directly discernible from wind-tunnel tests alone. Data are presented to show how the characteristics of a model tested in a wind tunnel are affected by power. The response of an airplane to a rolling and a yawing disturbance is discussed, particularly in regard to changes in wing dihedral and fin area. Solutions of the lateral equations of motion are given in a form suitable for direct computations. An approximate formula is developed that permits the rapid estimation of the accelerations produced during pull-up maneuvers involving abrupt elevator deflections.
Contributing Partner: UNT Libraries Government Documents Department
Effects of some present-day airplane design trends on requirements for lateral stability

Effects of some present-day airplane design trends on requirements for lateral stability

Date: June 1, 1941
Creator: Bamber, Millard J
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 circular shell-supported frames

Analysis of circular shell-supported frames

Date: January 1, 1944
Creator: Combs, Henry; Mignot, J E & Ensrud, A F
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Clamped long rectangular plate under combined axial load and normal pressure

Clamped long rectangular plate under combined axial load and normal pressure

Date: June 1, 1946
Creator: Woolley, Ruth M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Transition between laminar and turbulent flow by transverse contamination

Transition between laminar and turbulent flow by transverse contamination

Date: March 1, 1943
Creator: Charters, Alex C , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The photoviscous properties of fluids

The photoviscous properties of fluids

Date: February 1, 1942
Creator: Weller, R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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