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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
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
A method for calculating heat transfer in the laminar flow region of bodies

A method for calculating heat transfer in the laminar flow region of bodies

Date: December 1, 1942
Creator: Look, Bonne C
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
NACA Investigation of a Jet-Propulsion System Applicable to Flight

NACA Investigation of a Jet-Propulsion System Applicable to Flight

Date: April 1, 1944
Creator: Brown, Clinton E.
Description: Following a brief history of the NACA investigation of jet-propulsion, a discussion is given of the general investigation and analyses leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight-performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made. It was found that the main fire could be restricted to an intense, small, and short annular blue flame burning steadily and under control in the intended combustion space. With these readily obtainable combustion conditions, the combustion chamber the nozzle walls and the surrounding structure could be maintained at normal temperatures. The system investigated was found to be capable of burning one-half the intake air up the fuel rates of 3 pounds per second. Calculations were shown to agree well with experiment. It was concluded that the basic features of the jet-propulsion system investigation in the ground-test mock-up were ...
Contributing Partner: UNT Libraries Government Documents Department
A Concise Theoretical Method for Profile-Drag Calculation; Advance Report

A Concise Theoretical Method for Profile-Drag Calculation; Advance Report

Date: February 1, 1944
Creator: Nitzberg, Gerald E.
Description: In this report a method is presented for the calculation of the profile drag of airfoil sections. The method requlres only a knowledge of the theoretical velocity distribution and can be applied readily once this dlstribution is ascertained. Comparison of calculated and experimental drag characteristics for several airfoils shows a satisfactory agreement. Sample calculatlons 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
Determination of general relations for the behavior of turbulent boundary layers

Determination of general relations for the behavior of turbulent boundary layers

Date: July 1, 1943
Creator: Tetervin, Neal
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
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
Ditching tests with 1/10-size model of the Army A-20A airplane I : calm-water tests in NACA tank no.2

Ditching tests with 1/10-size model of the Army A-20A airplane I : calm-water tests in NACA tank no.2

Date: November 1, 1943
Creator: Jarvis, George A
Description: None
Contributing Partner: UNT Libraries Government Documents Department