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Some Effects of Compressibility on the Flow Through Fans and Turbines

Description: "The laws of conservation of mass, momentum, and energy are applied to the compressible flow through a two-dimensional cascade of airfoils. A fundamental relation between the ultimate upstream and downstream flow angles, the inlet Mach number, and the pressure ratio across the cascade is derived. Comparison with the corresponding relation for incompressible flow shows large differences. The fundamental relation reveals two ranges of flow angles and inlet Mach numbers, for which no ideal pressur… more
Date: August 1, 1945
Creator: Perl, W. & Epstein, H. T.
Item Type: Refine your search to only Report
open access

Mechanism of Start and Development of Aircraft Crash Fires

Description: "Full-scale aircraft crashes were made to investigate the mechanism of the start and development of aircraft crash fires. The results are discussed herein. This investigation revealed the characteristics of the ignition sources, the manner in which the combustibles spread, the mechanism of the union of the combustibles and ignition sources, and the pertinent factors governing the development of a crash fire as observed in this program" (p. 547).
Date: August 1, 1952
Creator: Pinkel, I. Irving; Preston, G. Merritt & Pesman, Gerard J.
Item Type: Refine your search to only Report
open access

Pressure distribution over the fuselage of a PW-9 pursuit airplane in flight

Description: "This report presents the results obtained from pressure distribution tests on the fuselage of a PW-9 pursuit airplane in a number of conditions of flight. The investigation was made to determine the contribution of the fuselage to the total lift in conditions considered critical for the wing structure, and also to determine whether the fuselage loads acting simultaneously with the maximum tail loads were of such a character as to be of concern with respect to the structural design of other par… more
Date: August 1, 1930
Creator: Rhode, Richard V. & Lundquist, Eugene E.
Item Type: Refine your search to only Report
open access

A Method of Estimating the Knock Rating of Hydrocarbon Fuel Blends

Description: "The usefulness of the knock ratings of pure hydrocarbon compounds would be increased if some reliable method of calculating the knock ratings of fuel blends was known. The purpose of this study was to investigate the possibility of developing a method of predicting the knock ratings of fuel blends. Two blending equations have been derived from an analysis based on certain assumptions relative to the cause of fuel knock" (p. 1).
Date: August 1, 1943
Creator: Sanders, Newell D.
Item Type: Refine your search to only Report
open access

A visual photographic study of cylinder lubrication

Description: From Summary: "A V-type engine provided with a glass cylinder was used to study visually the lubrication characteristics of an aircraft-type piston. Photographs and data were obtained with the engine motored at engine speeds up to 1000 r.p.m. and constant cylinder-head pressures of 0 and 50 pounds per square inch. A study was made of the orientation of the piston under various operating conditions, which indicated that the piston was inclined with the crown nearest the major-thrust cylinder fac… more
Date: August 1, 1945
Creator: Shaw, Milton C. & Nussdorfer, Theodore
Item Type: Refine your search to only Report
open access

Performance of NACA eight-stage axial-flow compressor designed on the basis of airfoil theory

Description: "The NACA has conducted an investigation to determine the performance that can be obtained from a multistage axial-flow compressor based on airfoil research. A theory was developed; an eight-stage axial-flow compressor was designed, constructed, and tested. The performance of the compressor was determined for speeds from 5000 to 14,000 r.p.m with varying air flow at each speed" (p. 81).
Date: August 1, 1944
Creator: Sinnette, John T., Jr.; Schey, Oscar W. & King, J. Austin
Item Type: Refine your search to only Report
open access

Theoretical study of the transonic lift of a double-wedge profile with detached bow wave

Description: "A theoretical study is described of the aerodynamic characteristics at small angle of attack of a thin, double-wedge profile in the range of supersonic flight speed in which the bow wave is detached. The analysis is carried out within the framework of the transonic (nonlinear) small-disturbance theory, and the effects of angle of attack are regarded as a small perturbation on the flow previously calculated at zero angle. The mixed flow about the front half of the profile is calculated by relax… more
Date: August 1, 1952
Creator: Vincenti, Walter G. & Wagoner, Cleo B.
Item Type: Refine your search to only Report
open access

A study of the zero-lift drag-rise characteristics of wing-body combinations near the speed of sound

Description: "Comparisons have been made of the shock phenomena and drag-rise increments for representative wing and central-body combinations with those for bodies of revolution having the same axial developments of cross-sectional areas normal to the airstream. On the basis of these comparisons, it is concluded that near the speed of sound the zero-lift drag rise of a low-aspect-ratio thin-wing and body combination is primarily dependent on the axial development of the cross-sectional areas normal to the … more
Date: August 1, 1952
Creator: Whitcomb, Richard T.
Item Type: Refine your search to only Report
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