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Effect of Propeller-Axis Angle of Attack on Thrust Distribution Over the Propeller Disk in Relation to Wake-Survey Measurement of Thrust

Description: "Tests were made to investigate the variation of thrust distribution over the propeller disk with angle of pitch of the propeller thrust axis and to determine the disposition and the minimum number of rakes necessary to measure the propeller thrust. The tests were made at a low Mach number for a low and a high blade angle with the propeller operating at three small angles of pitch, and some of the tests were repeated at a higher Mach number. The data obtained show that, for small angles of pitc… more
Date: December 1945
Creator: Pendley, Robert E.
Partner: UNT Libraries Government Documents Department
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The Effect of Internal Pressure on the Buckling Stress of Thin-Walled Circular Cylinders Under Torsion

Description: "The results of a series of tests to determine the effect of internal pressure on the buckling load of a thin cylinder under an applied torque indicated that internal pressure raises the shear buckling stress. The experimental results were analyzed with the aid of previously developed theory and a simple interaction formula was derived" (p. 1).
Date: May 1944
Creator: Crate, Harold; Batdorf, S. B. & Baab, George W.
Partner: UNT Libraries Government Documents Department
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Torsion Tests of Stiffened Circular Cylinders

Description: "The design of curved sheet panels to resist shear involves a consideration of several factors: the buckling resistance of the sheet, the stress at which buckling becomes permanent, and the strength which may be developed beyond the buckling limit by tension-field action. Although some experimental as well as theoretical work has been done on the buckling and tension-field phases of this problem, neither of these types of action appears to be very well understood. This report presents the resul… more
Date: May 1944
Creator: Moore, R. L. & Wescoat, C.
Partner: UNT Libraries Government Documents Department
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Investigation of Flow in an Axially Symmetrical Heated Jet of Air

Description: The work done under this contract falls essentially into two parts: the first part was the design and construction of the equipment and the running of preliminary tests on the 3-inch jet, carried out by Mr. Carl Thiele in 1940; the second part consisting in the measurement in the 1-inch jet flow in an axially symmetrical heated jet of air.
Date: December 1943
Creator: Corrsin, Stanley
Partner: UNT Libraries Government Documents Department
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Representative Operating Charts of Propellers Tested in the NACA 20-Foot Propeller-Research Tunnel

Description: Report presents the results of tests of full-scale propellers made in the 20-foot propeller-research tunnel (PRT) at the Langley Memorial Aeronautical Laboratory. The power coefficients of all dual-rotating propellers in the report represent the sum of the power coefficients of the front and rear propellers and are for the test conditions in which blade angles of the front and rear propellers were set to absorb approximately equal power at peak efficiency only.
Date: September 1943
Creator: Gray, W. H. & Mastrocola, Nicholas
Partner: UNT Libraries Government Documents Department
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Effect of normal pressure on the critical compressive and shear stress of curved sheet

Description: Results are presented of tests of two sets of 20 curved-sheet specimens to determine the effect of normal pressure on the critical compressive and shear stress of curved sheets. It was found that normal pressure raised the critical compressive and shear stress of curved sheets except when outward bulging occurred in compression, in which case the critical stress was lowered by normal pressure. (author).
Date: March 1945
Creator: Rafel, Norman & Sandlin, Charles W., Jr.
Partner: UNT Libraries Government Documents Department
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Generalized selection charts for bombers powered by two, four, and six 3000-horsepower engines 1: capacity and economy

Description: Supplement using data from a previous report to show the cargo that can be carried at various ranges, pounds of cargo that can be carried per pound of fuel, and other graphs to simplify the problem of determining which cargo can be carried at any range. The assumptions, parameters, and equations from the original report are carried over in the supplement.
Date: January 1943
Creator: Brevoort, Maurice J.; Stickle, George W. & Hill, Paul R.
Partner: UNT Libraries Government Documents Department
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Determination of Induced Velocity in Front of an Inclined Propeller by a Magnetic-Analogy Method

Description: Report presenting the horizontal and vertical components of the induced velocity in front of an inclined propeller in a horizontal stream obtained by a magnetic-analogy method. The problem was formulated in terms of the linear theory of the acceleration potential of an incompressible nonviscous fluid.
Date: February 1946
Creator: Gardner, Clifford S. & LaHatte, James A., Jr.
Partner: UNT Libraries Government Documents Department
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The longitudinal stability of flying boats as determined by tests of models in the NACA tank 1: methods used for the investigation of longitudinal stability characteristics

Description: Report presenting testing of dynamic models that has been helpful in the determination of the longitudinal stability characteristics on the water of a number of specific flying boats. Results regarding the constant-speed tests, accelerated runs, effect of variations in moment of inertia, effect of variations in mass moving vertically, effect of variations of depth of step, and effect of variations of gross load coefficient are provided.
Date: November 1942
Creator: Olson, Roland E. & Land, Norman S.
Partner: UNT Libraries Government Documents Department
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Full-Scale Tunnel Tests of a Flying Model of the Curtiss XP-55 Airplane

Description: Report presenting testing in the full-scale tunnel to provide data for estimating the longitudinal stability and control characteristics of the Curtis XP-55 airplane. Testing included lift, drag, pitching-moment, hinge-moment, and elevator pressure measurements for various combinations of angle of attack, elevator deflection, and elevator tab settings. The results of the force tests and some correlation of the results of the force tests and the pressure measurements are presented in the report.
Date: January 1943
Creator: Biebel, William J.
Partner: UNT Libraries Government Documents Department
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The Influence of Exhaust Pressure on Knock-Limited Performance

Description: Report discussing testing on two types of single cylinders to determine the effect of the relation of exhaust pressure to inlet-air pressure on knock-limited performance. Variables explored included exhaust pressure, fuel-air ratio, and engine speed. Three types of fuels were also used to explore the effect of exhaust pressure on fuel ratings.
Date: January 5, 1945
Creator: Cook, Harvey A.; Held, Louis F. & Pritchard, Ernest I.
Partner: UNT Libraries Government Documents Department
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An investigation of aircraft heaters 12: performance of a formed-plate crossflow exhaust gas and air heat exchanger

Description: Report presenting performance data on a Trane exhaust gas and air heat exchanger. Heat transfer rates were measured using specified exhaust gas rates and ventilating-air rates. The measured thermal outputs and static pressure drops are compared with predicted magnitudes.
Date: May 1943
Creator: Boelter, L. M. K.; Dennison, H. G.; Guibert, A. G. & Morrin, E. H.
Partner: UNT Libraries Government Documents Department
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Correlation of Wright Aeronautical Corporation Cooling Data on the R-3350-14 Intermediate Engine and Comparison With Data From the Langley 16-Foot High-Speed Tunnel

Description: Report presenting a comparison of the cooling-test data obtained on the identical Wright R-3350-14 engine equipped with the same cooling pressure-tube installation. The comparison reveals the large difference in cooling pressure drop that may be obtained in different test installations with the identical engine and pressure-tube installation because of an injudicious choice of pressure-tube locations.
Date: January 1945
Creator: Pinkel, Benjamin & Rubert, Kennedy F.
Partner: UNT Libraries Government Documents Department
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Cooling Tests of an Air-Cooled Engine Cylinder With Copper Fins on the Barrel

Description: Report presenting the results of comparative cooling tests run on two Wright C9GC (G-200) cylinders, one with the original steel fins and one with 1-inch spiral copper fins brazed on the barrel. Calculations were also performed using copper and aluminum fins with the same weight as the original steel fins, which showed positive results. Results regarding cylinder-temperature correlation, piston-temperature correlation, and comparative performance are also provided.
Date: July 1942
Creator: Sanders, J. C.; Wilsted, H. D. & Mulcahy, B. A.
Partner: UNT Libraries Government Documents Department
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Investigations on Laminar Boundary-Layer Stability and Transition on Curved Boundaries

Description: Report presenting an investigation of the transition of the boundary layer from the laminar to the turbulent region on a flat plate, on the concave and convex side of a plate with a 20-foot radius of curvature, and on the convex side of a plate with a 30-inch radius of curvature.
Date: May 1946
Creator: Liepmann, Hans W.
Partner: UNT Libraries Government Documents Department
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