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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Technical Notes
 Collection: Technical Report Archive and Image Library
The variation in pressure in the cabin of an airplane in flight

The variation in pressure in the cabin of an airplane in flight

Date: March 1, 1931
Creator: Gough, Melvin N
Description: The pressure in the cabin of a Fairchild cabin monoplane wa surveyed in flight, and was found to decrease with increased air speed over the fuselage and to vary with the number and location of openings in the cabin. The maximum depression of 2.2 inches of water (equivalent pressure altitude at sea level of 152 feet) occurred at the high speed of the airplane in level flight with the cabin closed.
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
An approximate spin design criterion for monoplanes

An approximate spin design criterion for monoplanes

Date: June 1, 1939
Creator: Donlan, Charles J & Seidman, Oscar
Description: A quantitative criterion of merit has been needed to assist airplane designers to incorporate satisfactory spinning characteristics into new designs. An approximate empirical criterion, based on the projected side area and the mass distribution of the airplane, has been formulated in a recent British report. In the present paper, the British results have been analyzed and applied to American designs. A simpler design criterion based solely on the type and the dimensions of the tail, has been developed: it is useful in a rapid estimation of whether a new design is likely to comply with the minimum requirements for safety in spinning.
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
Principal Effects of Axial Load on Moment-Distribution Analysis of Rigid Structures

Principal Effects of Axial Load on Moment-Distribution Analysis of Rigid Structures

Date: July 1, 1935
Creator: James, Benjamin Wylie
Description: This thesis presents the method of moment distribution modified to include the effect of axial load upon the bending moments. This modification makes it possible to analyze accurately complex structures, such as rigid fuselage trusses, that heretofore had to be analyzed by approximate formulas and empirical rules. The method is simple enough to be practicable even for complex structures, and it gives a means of analysis for continuous beams that is simpler than the extended three-moment equation now in common use. When the effect of axial load is included, it is found that the basic principles of moment distribution remain unchanged, the only difference being that the factors used, instead of being constants for a given member, become functions of the axial load. Formulas have been developed for these factors, and curves plotted so that their applications requires no more work than moment distribution without axial load. Simple problems have been included to illustrate the use of the curves.
Contributing Partner: UNT Libraries Government Documents Department
Reciprocity relations in aerodynamics

Reciprocity relations in aerodynamics

Date: May 1, 1952
Creator: Spreiter, John R & Heaslet, Max A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Corrugated metal diaphragms for aircraft pressure-measuring instruments

Corrugated metal diaphragms for aircraft pressure-measuring instruments

Date: November 1, 1939
Creator: Goerke, V H & Wildhack, W A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A low-speed experimental investigation of the effect of a sandpaper type of roughness on boundary-layer transition

A low-speed experimental investigation of the effect of a sandpaper type of roughness on boundary-layer transition

Date: January 1, 1958
Creator: Horton, E. A. & Vondoenhoff, A. E.
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
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