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 Decade: 1940-1949
 Year: 1943
 Serial/Series Title: NACA Advanced Restricted Report
 Collection: National Advisory Committee for Aeronautics Collection
Aerodynamic and hydrodynamic tests of a family of models of flying-boat hulls derived from a streamline body : NACA model 84 series

Aerodynamic and hydrodynamic tests of a family of models of flying-boat hulls derived from a streamline body : NACA model 84 series

Date: September 1943
Creator: Luoma, Arvo A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Analysis of wind-tunnel stability and control tests in terms of flying qualities in full-scale airplanes

Analysis of wind-tunnel stability and control tests in terms of flying qualities in full-scale airplanes

Date: October 1943
Creator: Kayten, Gerald G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Charts for calculation of the critical stress for local instability of columns with I-, Z-, channel and rectangular-tube section

Charts for calculation of the critical stress for local instability of columns with I-, Z-, channel and rectangular-tube section

Date: November 1, 1943
Creator: Heimerl, George J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
A comparative study of the effect of wing flutter shape on the critical flutter speed

A comparative study of the effect of wing flutter shape on the critical flutter speed

Date: November 1, 1943
Creator: Pinkel, I Irving
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Construction of wire strain gages for engine application

Construction of wire strain gages for engine application

Date: December 1, 1943
Creator: Tucker, Maurice
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Correlation of single-cylinder cooling tests of a Pratt and Whitney R-2800-21 engine cylinder with wind-tunnel tests of a Pratt and Whitney R-2800-27 engine

Correlation of single-cylinder cooling tests of a Pratt and Whitney R-2800-21 engine cylinder with wind-tunnel tests of a Pratt and Whitney R-2800-27 engine

Date: December 1, 1943
Creator: Rollin, Vern G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Critical shear stress of an infinitely long flat plate with equal elastic restraints against rotation along the parallel edges

Critical shear stress of an infinitely long flat plate with equal elastic restraints against rotation along the parallel edges

Date: November 1, 1943
Creator: Stowell, Elbridge Z
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Critical stress for an infinitely long flat plate with elastically restrained edges under combined shear and direct stress

Critical stress for an infinitely long flat plate with elastically restrained edges under combined shear and direct stress

Date: November 1, 1943
Creator: Schwartz, Edward B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Critical stresses for plates

Critical stresses for plates

Date: October 1, 1943
Creator: Schuette, Evan H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Data on buckling strength of curved sheet in compression

Data on buckling strength of curved sheet in compression

Date: October 1, 1943
Creator: Levin, L Ross
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design criterions for the dimensions of the forebody of a long-range flying boat

Design criterions for the dimensions of the forebody of a long-range flying boat

Date: November 1, 1943
Creator: Parkinson, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design, selection, and installation of aircraft heat exchangers

Design, selection, and installation of aircraft heat exchangers

Date: July 1, 1943
Creator: Brevoort, Maurice J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of the damping moment in yawing for tapered wings with partial-span flaps

Determination of the damping moment in yawing for tapered wings with partial-span flaps

Date: August 1, 1943
Creator: Harmon, Sidney M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Development of thermal ice-prevention equipment for the B-17F airplane

Development of thermal ice-prevention equipment for the B-17F airplane

Date: August 1, 1943
Creator: Rodert, Lewis A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of compressibility on two-dimensional tunnel-wall interference for a symmetrical airfoil

The effect of compressibility on two-dimensional tunnel-wall interference for a symmetrical airfoil

Date: January 1, 1943
Creator: Nitzberg, Gerald E
Description: Summary: The effective change in the velocity of flow past a wing section, caused by the presence of wind-tunnel walls, is known for potential flow. This theory is extended by investigation of the two-dimensional compressible flow past a thin Rankine Oval. It is shown that for a symmetrical section at zero angle of attack the velocity increment due to the tunnel walls in the incompressible case must be multiplied by the factor 1/1-M^2 to take account of compressibility effects. The Mach number, M, corresponds to conditions in the wind-tunnel test section with the model removed (p. 1.).
Contributing Partner: UNT Libraries Government Documents Department
The effect of dead rise upon the high-angle porpoising characteristics of two planing surfaces in tandem

The effect of dead rise upon the high-angle porpoising characteristics of two planing surfaces in tandem

Date: June 1, 1943
Creator: Klein, Milton M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of length-beam ration on resistance and spray of three models of flying-boat hulls

Effect of length-beam ration on resistance and spray of three models of flying-boat hulls

Date: October 1, 1943
Creator: Zeck, Howard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel

The Effect of Mass Distribution on the Lateral Stability and Control Characteristics of an Airplane as Determined by Tests of a Model in the Free-Flight Tunnel

Date: August 1, 1943
Creator: Seacord, Charles L & Campbell, John P.
Description: The effects of mass distribution on lateral stability and control characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rolling and yawing movements of inertia were increased from normal values to values up to five times normal. For each moment-of-inertia condition, combinations of dihedral and vertical-tail area representing a variety of airplane configurations were tested. The results of the flight tests of the model were correlated with calculated stability and control characteristics and, in general, good agreement was obtained. The tests showed the following effects of increased rolling and yawing moments of inertia: no appreciable change in spiral stability; reductions in oscillatory stability that were serious at high values of dihedral; a reduction in the sensitivity of the model to gust disturbances; and a reduction in rolling acceleration provided by the ailerons, which caused a marked increase in time to reach a given angle of bank. The general flight behavior of the model became worse with increasing moments of inertia but, with combinations of small effective dihedral and large vertical-tail area, satisfactory flight characteristics were obtained at all moment-of-inertia conditions.
Contributing Partner: UNT Libraries Government Documents Department
Effect of pH on strength of resin bonds

Effect of pH on strength of resin bonds

Date: October 1, 1943
Creator: Kline, G. M.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of turbulence on air-flow measurements behind orifice plates

Effect of turbulence on air-flow measurements behind orifice plates

Date: July 1, 1943
Creator: Nielsen, Jack N
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of wing leading-edge slots on the spin and recovery characteristics of airplanes

Effect of wing leading-edge slots on the spin and recovery characteristics of airplanes

Date: April 1, 1943
Creator: Pitkin, Marvin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of wing loading and altitude on lateral stability and control characteristics of an airplane as determined by tests of a model in the free-flight tunnel

Effect of wing loading and altitude on lateral stability and control characteristics of an airplane as determined by tests of a model in the free-flight tunnel

Date: June 1, 1943
Creator: Seacord, Charles L , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental determination of the yawing moment due to yawing contributed by the wing, fuselage, and vertical tail of a midwing airplane model

Experimental determination of the yawing moment due to yawing contributed by the wing, fuselage, and vertical tail of a midwing airplane model

Date: June 1, 1943
Creator: Mathews, Ward O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Investigation of Entrance-Region Heat-Transfer Coefficients

Experimental Investigation of Entrance-Region Heat-Transfer Coefficients

Date: November 1, 1943
Creator: Joyner, Upshur T
Description: Experimental results of tests made at the Langley Memorial Aeronautical Laboratory are presented to show how heat-transfer coefficients can he increased by a method utilizing the high rate of heat transfer known to exist on any heat-transfer surface in the region adjacent to the edge on which the cooling or heating fluid impinges. The results show that, for the same pressure drop, the average surface heat-transfer.coefficient can be increased 50 to 100 percent when a cooling surface having a length of four inches in the direction of fluid flow is cut to form twenty fins with a length of 0.2 inch in the direction of fluid flow and the fins are sharpened and staggered in the air stream. The percentage of increase in the surface heat-transfer coefficient obtained as a result of shortening the length of the cooling surface varies with the pressure drop of the cooling fluid in passing the surface, the increase being largest when small pressure drop is used and smallest when high pressure drop is used.
Contributing Partner: UNT Libraries Government Documents Department
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