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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Longitudinal stability investigation of a vertical-take-off-and-landing airplane configuration with simulated jet intake and exhaust at Mach numbers of 1.61 and 2.01

Longitudinal stability investigation of a vertical-take-off-and-landing airplane configuration with simulated jet intake and exhaust at Mach numbers of 1.61 and 2.01

Date: January 30, 1958
Creator: Lord, Douglas R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effects of boundary-layer separation over bodies of revolution with conical tail flares

The effects of boundary-layer separation over bodies of revolution with conical tail flares

Date: December 12, 1957
Creator: Dennis, David H
Description: The magnitude and the effects of boundary-layer separation on normal-force-curve slopes, centers of pressure, pressure distributions, and lift and drag coefficients were determined for various bodies of revolution with conical tail flares at Mach numbers from 3.0 to 6.3. Some of the experimental results are compared to theoretical predictions of the aerodynamic characteristics of the bodies.
Contributing Partner: UNT Libraries Government Documents Department
Elevated-temperature combined stress-rupture plus fatigue strength of Waspaloy having different aging treatments and/or molybdenum contents

Elevated-temperature combined stress-rupture plus fatigue strength of Waspaloy having different aging treatments and/or molybdenum contents

Date: February 25, 1958
Creator: Hoffman, C A & Hornak, M B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model Between Mach Numbers of 0.81 and 1.64: TED No. NACA AD 399

Effects of Inlet Modification and Rocket-Rack Extension on the Longitudinal Trim and Low-Lift Drag of the Douglas F5D-1 Airplane as Obtained with a 0.125-Scale Rocket-Boosted Model Between Mach Numbers of 0.81 and 1.64: TED No. NACA AD 399

Date: June 5, 1957
Creator: Hastings, Earl C., Jr. & Dickens, Waldo L.
Description: A flight investigation was conducted to determine the effects of inlet modification and rocket-rack extension on the longitudinal trim and low-lift drag of the Douglas F5D-1 airplane. The investigation was conducted with a 0.125-scale rocket-boosted model between Mach Numbers of 0.81 and 1.64. This paper presents the changes in trim angle of attack, trim lift coefficient, and low-lift drag caused by the modified inlets alone over a small part of the test Mach number range and by a combination of the modified inlets and extended rocket racks throughout the remainder of the test.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of Operating Characteristics of an Engine Equipped with Modifications to Eliminate Fuel-Evaporation Icing

Investigation of Operating Characteristics of an Engine Equipped with Modifications to Eliminate Fuel-Evaporation Icing

Date: December 24, 1946
Creator: Mulholland, Donald R. & Zlotowski, Edward D.
Description: Two modified fuel-injection systems, a drilled-inducer type and a spinner type, that prevent serious fuel-evaporation icing were installed on a V-type, liquid-cooled aircraft engine and a preliminary investigation was conducted to determine the effect on engine operating characteristics. The spinner system was also ground - and flight tested on a twin-engine fighter airplane. Flight measurements of cylinder-head temperature over a range of fuel-air ratios and engine power conditions were made at an altitude of approximately 10,000 feet. Starting and accelerating of the engine on the ground were unaffected by the fuel-injection modifications. During the flight investigation, no appreciable variation occurred between the maximum and minimum cylinder-head temperature with the standard and modified system for the same power condition and no irregularity of mixture distribution could be detected throughout the power range of the engine. Normal mixture distribution was also indicated by a similar response of cylinder-head temperature for variations of fuel-air ratio at manifold pressures of 25 and 35 inches of mercury absolute. Both modified fuel-injection systems required less fuel-nozzle pressure than the standard system to obtain the desired fuel-air ratio for given air-flow condition.
Contributing Partner: UNT Libraries Government Documents Department
Some Experiences Regarding the Nonlinearity of Hot Wires

Some Experiences Regarding the Nonlinearity of Hot Wires

Date: June 1, 1952
Creator: Betchov, R. & Welling, W.
Description: We compare here the results of some experiences with the formulas established in our preceding report 'Nonlinear Theory of a Hot-Wire Anemometer.' We shall show that the nonlinear term plays a role as important as the thermal conduction in the calculation of the thermal inertia of the hot wire.
Contributing Partner: UNT Libraries Government Documents Department
Turbulent Skin Friction at High Mach Numbers and Reynolds Numbers

Turbulent Skin Friction at High Mach Numbers and Reynolds Numbers

Date: July 24, 1958
Creator: Matting, Fred W. & Chapman, Dean R.
Description: For a number of years now, experimenters have been making measurements of skin friction. Formerly, the main interest was at low Mach numbers; later, measurements were made at supersonic Mach numbers. However, almost all of these measurements were over a limited range of Reynolds numbers. On the other hand, these measurements fairly well determined the effects of Mach number and heat transfer on skin friction. The purpose of this paper is to give the results of skin-friction measurements in turbulent boundary layers at high Mach numbers and high Reynolds numbers where data have not previously existed. The equipment used was expressly designed to provide these conditions. As is well known, it is difficult to obtain high Mach numbers and high Reynolds numbers simultaneously with air in a wind tunnel. In order to avoid condensation, it is necessary to heat the air, with a resulting loss in density and Reynolds number. It is desirable, then, to use a gas that does not condense at high Mach numbers. This suggested helium, which was used as a working fluid in some of the tests. At high Mach numbers in a given wind tunnel, higher Reynolds numbers can be obtained with helium than with ...
Contributing Partner: UNT Libraries Government Documents Department
Investigation of an all-moveable control surface at a Mach number of 6.86 for possible flutter

Investigation of an all-moveable control surface at a Mach number of 6.86 for possible flutter

Date: May 8, 1958
Creator: Lauten, William T , Jr; Levey, Gilbert M & Armstrong, William O
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Results of a Flight Investigation of 1/6-Scale Rocket-Powered Models of the Bell MX-776 to Determine Aileron Rolling Effectiveness and Total Drag

Preliminary Results of a Flight Investigation of 1/6-Scale Rocket-Powered Models of the Bell MX-776 to Determine Aileron Rolling Effectiveness and Total Drag

Date: January 1, 1950
Creator: Stevens, Joseph E.
Description: An experimental investigation of the variation of aileron rolling effectiveness and total drag with Mach number has been made using 1/6-scale rocket-propelled models of the Bell MX-776. Three models having constant-chordwise-thickness full-span aileron at approximate deflections of 2 deg, 5 deg, and 15 deg have been flown. Positive control effectiveness over the Mach number range between approximately 0.5 and 1.2 was obtained from the models and no indication of reversal of effectiveness was encountered. The ratio of tip helix angle to aileron deflection indicated a decrease in proportional rolling effectiveness with increasing deflections in the Mach number range from approximately 0.7 to 1.0. A drag rise of about 125 percent in the transonic region between Mach numbers of 0.85 and 1.02 followed by a gradual decrease at higher speeds was revealed.
Contributing Partner: UNT Libraries Government Documents Department
Comparative Results of Tests on Several Different Types of Nozzles

Comparative Results of Tests on Several Different Types of Nozzles

Date: May 1, 1944
Creator: Kisenko, M. S.
Description: This paper presents the results of tests conducted to determine the effect of the constructional elements of a Laval nozzle on the velocity and pressure distribution and the magnitude of the reaction force of the jet. The effect was studied of the shapes of the entrance section of the nozzle and three types of divergent sections: namely, straight cone, conoidal with cylindrical and piece and diffuser obtained computationally by a graphical method due to Professor F. I. Frankle. The effect of the divergence angle of the nozzle on the jet reaction was also investigated. The results of the investigation showed that the shape of the generator of the inner surface of the entrance part of the nozzle essentially has no effect on the character of the flow and on the reaction. The nozzle that was obtained by graphical computation assured the possibility of obtaining a flow for which the velocity of all the gas particles is parallel to the axis of symmetry of the nozzle, the reaction being on the average 2 to 3 percent greater than for the usual conical nozzle under the same conditions, For the conical nozzle the maximum reaction was obtained for a cone angle of ...
Contributing Partner: UNT Libraries Government Documents Department