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Aerodynamic Characteristics of Bodies at Supersonic Speeds: A Collection of Three Papers

Description: The three papers collected here are: 'The Effect of Nose Shape on the Drag of Bodies of Revolution at Zero Angle of Attack.', 'Base Pressure on Wings and Bodies with Turbulent Boundary Layers', and 'Flow over Inclined Bodies'. The subject of the first paper is the drag of the nose section of bodies of revolution at zero angle of attack. The main object of the second paper is to summarize the prinicpal results of the many wind tunnel and free flight measurements of base pressure on both bodies of revolution and blunt trailing edge airfoils.
Date: November 9, 1951

Aerodynamic Design of Axial-Flow Compressors. 7 - Blade-Element Flow in Annular Cascades

Description: Annular blade-element data obtained primarily from single-stage compressor installations are correlated over a range of inlet Mach numbers and cascade geometry. The correlation curves are presented in such a manner that they are related directly to the low-speed two-dimensional-cascade data of part VI of this series. Thus, the data serve as both an extension and a verification of the two-dimensional-cascade data. In addition, the correlation results are applied to compressor design.
Date: August 9, 1955
Creator: Robbins, William H.; Jackson, Robert J. & Lieblein, Seymour

Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees: effect of Reynolds number at supersonic Mach numbers on the longitudinal characteristics of a wing twisted and cambered for uniform load

Description: Report presenting a wind-tunnel investigation of the longitudinal characteristics of a wing-body combination with a wing with leading edge swept back 63 degrees. Lift, drag, and pitching-moment measurements were made over a range of Mach and Reynolds numbers. Results regarding the general characteristics and effect of Reynolds number are provided.
Date: October 9, 1950
Creator: Heitmeyer, John C.

Aeronautical study of a wing-fuselage combination employing a wing swept back 63 degrees: Characteristics at supersonic speeds of a model with the wing twisted and cambered for uniform load

Description: Report presenting the lift, drag, and pitching-moment characteristics of a wing-fuselage combination employing a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at a lift coefficient of 0.25 and Mach number 1.53. The experimental results are compared to those from other investigations. A maximum lift-drag ratio of 8.9 and a minimum drag coefficient of 0.0145 was obtained.
Date: January 9, 1950
Creator: Hall, Charles F. & Heitmeyer, John C.

Aircraft-Fuel-Tank Design for Liquid Hydrogen

Description: Some of the considerations involved in the design of aircraft fuel tanks for liquid hydrogen are discussed herein. Several of the physical properties of metals and thermal insulators in the temperature range from ambient to liquid-hydrogen temperatures are assembled. Calculations based on these properties indicate that it is possible to build a large-size liquid-hydrogen fuel tank which (1) will weigh less then 15 percent of the fuel weight, (2) will have a hydrogen vaporization rate less than 30 percent of the cruise fuel-flow rate, and (3) can be held in a stand-by condition and readied for flight in a short time.
Date: August 9, 1955
Creator: Reynolds, T. W.

Altitude-chamber investigation of J73-GE-1A turbojet engine component performance

Description: Report presenting an investigation to determine the altitude performance characteristics of a J73-GE-1A turbojet engine conducted in an altitude chamber. The engine had a ten-percent oversize turbine-nozzle are compared with the production J73 engine. Results regarding radial pressure and temperature profiles, compressor performance, combustor performance, turbine performance, and tail-pipe-diffuser and exhaust-nozzle performance.
Date: December 9, 1954
Creator: Campbell, Carl E. & Sobolewski, Adam E.

Altitude Performance Characteristics of the J73-GE-1A Turbojet Engine

Description: From Introduction: "The over-all altitude-performance characteristics of this engine are reported herein, and the component performance characteristics are given in reference 1. The data are presented in the form of engine pumping characteristics to allow accurate calculation of engine performance at any operating or flight condition within the range covered by the experimental data. A curve is also presented that will allow determination of thrust in flight by the measurement of ambient static pressure and total pressure in the exhaust nozzle."
Date: December 9, 1954
Creator: Campbell, Carl E. & Conrad, E. William

Altitude-Test-Chamber Investigation of the Endurance and Performance Characteristics of the J65-W-7 Engine at a Mach Number of 2.0

Description: An investigation of the endurance characteristics, at high Mach number, of the J65-W-7 engine was made in an altitude chamber at the Lewis laboratory. The investigation was made to determine whether this engine can be operated at flight conditions of Mach 2 at 35,000-feet altitude (inlet temperature, 250 F) as a limited-service-life engine Failure of the seventh-stage aluminum compressor blades occurred in both engines tested and was attributed to insufficient strength of the blade fastenings at the elevated temperatures. For the conditions of these tests, the results showed that it is reasonable to expect 10 to 15 minutes of satisfactory engine operation before failure. The high temperatures and pressures imposed upon the compressor housing caused no permanent deformation. In general, the performance of the engines tested was only slightly affected by the high ram conditions of this investigation. There was no discernible depreciation of performance with time prior to failure.
Date: February 9, 1955
Creator: Biermann, A. E. & Braithwaite, Willis M.

Analysis of heat transfer and fluid friction for fully developed turbulent flow of supercritical water with variable fluid properties in a smooth tube

Description: From Summary: "Calculated velocity and temperature distributions, as well as relations among Nusselt number, Reynolds number, and friction factor, are presented. The effect of variation of fluid properties across the tube on the Nusselt number and friction factor correlations can be eliminated by evaluating the properties at a reference temperature which is a function of both the wall temperature and the ratio of wall-to-bulk temperatures."
Date: April 9, 1953
Creator: Deissler, Robert G & Taylor, Maynard F

Analysis of longitudinal stability and trim of the Bell X-1 airplane at a lift coefficient of 0.3 to Mach numbers near 1.05

Description: Report presenting flight test data obtained with two Bell X-1 airplanes, one with an 8-percent-thick wing and a 6-percent-thick tail and one with a 10-percent-thick wing and an 8-percent-thick tail. Data was obtained at a variety of Mach numbers, lift coefficients, and test altitudes. Results regarding stick-fixed stability and trim changes are provided.
Date: October 9, 1951
Creator: Drake, Hubert M.; Carden, John R. & Clagett, Harry P.

Analysis of Low-Temperature Nuclear-Powered Ram-Jet Missile for High Altitudes

Description: Report presenting the gross weight and uranium investment of nuclear-powered, direct-air, shieldless, ram-jet missiles for a range of altitudes and Mach numbers. Results regarding the effect of reactor operating conditions and flight conditions on ramjet performance and effect of assumptions on ramjet performance are provided.
Date: November 9, 1955
Creator: Sams, Eldon W. & Rom, Frank E.

Analysis of low-temperature nuclear-powered ramjet missile for high altitudes

Description: From Summary: "The reactor operating conditions were varied to enable selection of values giving a good compromise between low uranium investment and loss gross weight at each altitude and flight Mach number considered. The corresponding values of reactor and missile operating conditions are presented in the report."
Date: November 9, 1955
Creator: Rom, F. E. & Sams, E. W.

Analysis of rocket, ram-jet, and turbojet engines for supersonic propulsion of long-range missiles 1: rocket-engine performance

Description: Report presenting theoretical performance characteristics and estimates of effective specific impulse and weight for rocket engines serving a main and booster power plants for missiles. The fuels used included ammonia-fluorine and JP4-oxygen propellants. At extremely high altitudes, the specific impulse depends primarily on the expansion ratio.
Date: July 9, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack

An analysis of the potentialities of a two-stage counterrotating supersonic compressor

Description: From Introduction: "The supersonic axial-flow compressor, for example, appears to offer advantages of high stage pressure ratio and height weight flows (reference 1) but problems peculiar to this compressor type have accompanied its introduction. For high single-stage pressure ratios (>4) the problem of converting the high dynamic energy to useful pressure arises (reference 2). In addition, the high tip speeds and weight flows combine to create a difficult situation for the turbine designer."
Date: July 9, 1952
Creator: Wilcox, Ward W.

Analysis of Turbine Stator Adjustment Required for Compressor Design-Point Operation in High Mach Number Supersonic Turbojet Engines

Description: From Introduction: "An investigation of the variation in turbine-entrance equivalent weight flow for a two-stage turbine equipped with an adjustable turbine stator is presented in reference 1. A general analytical investigation of turbine stator adjustment is presented in reference 2. In reference 2, the effect of stator adjustment on turbine off-design performance is also investigated by analytically computing the performance of a particular single-stage turbine."
Date: October 9, 1953
Creator: English, Robert E. & Cavicchi, Richard H.

Analytical studies of the response to longitudinal control of three airplane configurations in landing approaches

Description: From Introduction: "A theoretical investigation was conducted in order to determine what effect the differences in aerodynamic characteristics would have on the short-time response to elevator control of this type of airplane as compared with the responses of a conventional airplane, without regard to any possible psychological influences. The results of this investigation are presented in this paper."
Date: April 9, 1953
Creator: Bihrle, William, Jr. & Stone, Ralph W., Jr.

An analytical study of the comparative performance of six air-induction systems for turbojet-powered airplanes designed to operate at Mach numbers up to 2.0

Description: Report presenting an extension of NACA RM A52C14 about inlet design and performance for Mach numbers of 1.5 to 2.0. A two-dimensional inviscid analysis is used to compare the performance of several types of inlets when used in conjunction with a turbojet engine with constant-volume air flow. Results regarding air delivery and air requirements, drag factors, evaluation of inlet performance, significance of the drag summation, and inlet and engine-matching considerations are provided.
Date: October 9, 1953
Creator: Watson, Earl C.

A balanced-pressure sliding seal used for transfer of pressurized air between stationary and rotating parts

Description: A combination sliding-ring and pressure-balancing seal capable of transferring pressurize air from stationary to rotating parts was developed and experimentally investigated at sliding velocities and cooling-air pressures up to 10,000 feet per minute and 38.3 pounds per square inch absolute, respectively. Leakage of cooling air was completely eliminated with an expenditure of balance air less than one-fourth the leakage loss of air from labyrinth seals under the same conditions. Additional cooling of the carbon-base seal rings was required, and the maximum wear rate on the rings was about 0.0005 inch per hour.
Date: January 9, 1957
Creator: Curren, Arthur N. & Cochran, Reeves P.

Comparison of experimental with theoretical total-pressure loss in parallel-walled turbojet combustors

Description: "An experimental investigation of combustor total-pressure loss was undertaken to confirm previous theoretical analyses of effects of geometric and flow variables and of heat addition. The results indicate that a reasonable estimate of cold-flow total-pressure-loss coefficient may be obtained from the theoretical analyses. Calculated total-pressure loss due to heat addition agreed with experimental data only when there was no flame ejection from the liner at the upstream air-entry holes" (p. 1).
Date: January 9, 1957
Creator: Dittrich, Ralph T.

Component Tests to Determine the Aerodynamic Characteristics of an All-Moveable 70 Degree Delta Canard-Type Control in the Presence of a Body at a Mach Number of 1.61

Description: Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics of a body-control arrangement at Mach number 1.61. A 70 degree delta canard-type control mounted in the horizontal plane and with a span-to-body-diameter ratio at the control trailing edge of 2.52 tested both fixed and moving in the presence of a long cylindrical body with a parabolic nose.
Date: October 9, 1953
Creator: Spearman, M. Leroy