190 Matching Results

Search Results

Investigation of engine performance and high-temperature properties of precision-cast turbine blades of high carbon Stellite 21 and controlled grain-size-Stellite 21

Description: Report presenting an investigation to determine the effect of controlled grain size and increased carbon content on engine performance and high-temperature properties of precision-cast Stellite 21 turbine blades. Results regarding blade stresses, engine operation, and metallurgical examination are provided.
Date: June 23, 1952
Creator: Yaker, Charles; Garrett, Floyd B. & Sikora, Paul F.
Partner: UNT Libraries Government Documents Department

A flight and analog computer study of some stabilization and command networks for an automatically controlled interceptor during the final attack phase

Description: Report presenting studies of the final attack phase of an automatically controlled interceptor in flight and electronic simulators to investigate various airplane command and stabilization networks and to develop simple but adequate simulation techniques for the synthesis of automatic control systems. Results regarding automatic control with a simple command system, automatic control with the improved command system, and evaluation of the automatic control system in typical final attack maneuvers are provided.
Date: March 23, 1955
Creator: Turner, Howard L.; Triplett, William C. & White, John S.
Partner: UNT Libraries Government Documents Department

Flight measurements of the lateral stability and control characteristics of a high-speed fighter airplane

Description: Report presenting the results of a flight investigation of the lateral stability and control characteristics of a high-speed fighter airplane. Results regarding the control-free lateral oscillations, sideslip characteristics, rudder control characteristics, rudder hinge-moment characteristics, and rolling characteristics are provided.
Date: September 23, 1952
Creator: Crane, H. L.; Beckhardt, A. R. & Matheny, C. E.
Partner: UNT Libraries Government Documents Department

Investigation of a ramp-type inlet designed for improved angle-of-attack performance at Mach number 2.0

Description: Report presenting an investigation of an inlet mounted on the side of a fuselage and utilizing a horizontally oriented 14 degree ramp located at the top of the inlet at a variety of Mach numbers. The characteristics of this inlet were compared to a conventional ramp-type side inlet. Results regarding the pressure recovery and model drag coefficients, spillage drag coefficients, and thrust minus drag comparison are provided.
Date: February 23, 1955
Creator: Wise, G. A. & Campbell, R. C.
Partner: UNT Libraries Government Documents Department

Oscillating hinge moments and flutter characteristics of a flap-type control surface on a 4-percent-thick unswept wing with low aspect ratio at transonic speeds

Description: Report presenting free-oscillation tests to determine the dynamic hinge-moment characteristics of a trailing-edge flap-type control surface on a 4-percent-thick unswept wing with low aspect ratio. Tests were made over a range of Mach numbers, reduced frequencies, and low test speeds. Results regarding the effects of wing motion, damping moment and flutter characteristics, spring moments, and theoretical results are provided.
Date: February 23, 1956
Creator: Thompson, Robert F. & Moseley, William C., Jr.
Partner: UNT Libraries Government Documents Department

Longitudinal stability and control characteristics of a semispan airplane model with a sweptback wing and tail from tests at transonic speeds by the NACA wing-flow method

Description: Report presenting an investigation using the NACA wing-flow method to determine the longitudinal stability and control characteristics at transonic speeds of a semispan airplane with a 45 degree sweptback wing and tail. Measurements of the lift and angle of attack for trim were made for several stabilizer and elevator settings. Testing was also performed to investigate the effects of transition wires mounted on the wing and tail, the effect of increasing the boundary-layer thickness on the test surface, and the effectiveness of a wing flap with a sweepback of 45 degrees.
Date: July 23, 1948
Creator: Sawyer, Richard H. & Lina, Lindsay J.
Partner: UNT Libraries Government Documents Department

Evaluation of ethyl ether as an ignition aid for turbojet engine fuels

Description: Report presenting an investigation to determine the effectiveness of ethyl ether as an ignition aid for low-volatility turbojet-engine fuels. The minimum spark engines required to ignite a single J33 combustor over a range of altitude inlet-air pressures and flow rates with several fuel blends are provided.
Date: October 23, 1953
Creator: Jonash, Edmund R. & Foster, Hampton H.
Partner: UNT Libraries Government Documents Department

Operating temperatures of I-40-5 turbojet engine burner liners and the effect of temperature variation on burner-liner service life

Description: Report presenting an investigation of burner liners in a turbojet engine to determine the principal factors limiting the burner-liner service life. The investigation covered a range of engine speeds and testing was conducted to determine whether bare, ceramic-coated, or shielded thermocouples would give the most correct temperature readings.
Date: August 23, 1948
Creator: Wilsted, H. D.; Duffy, Robert T. & Grey, Ralph E.
Partner: UNT Libraries Government Documents Department

A limit pressure coefficient and an estimation of limit forces on airfoils at supersonic speeds

Description: Report presenting the results of an estimation of the limit forces on airfoils at supersonic speeds. The limit pressure coefficient attainable on an airfoil is shown to be about 70 percent of the pressure coefficient for a vacuum over a wide range of Mach numbers.
Date: August 23, 1948
Creator: Mayer, John P.
Partner: UNT Libraries Government Documents Department

Effect of control trailing-edge thickness or aspect ratio on the oscillating hinge-moment and flutter characteristics of a flap-type control at transonic speeds

Description: Report presenting free-oscillation tests in the high-speed tunnel to determine the effect of control trailing-edge thickness and control aspect ratio on the dynamic hinge-moment characteristics of a trailing-edge, flap-type control. Tests were made at a range of Mach numbers and a range of oscillation reduced frequency at an angle of attack of 0 degrees. Results regarding damping moments and flutter characteristics and spring moments are provided.
Date: April 23, 1958
Creator: Moseley, William C., Jr. & Thompson, Robert F.
Partner: UNT Libraries Government Documents Department

Correlation of creep-buckling tests with theory

Description: Report presenting the results of short-time creep-buckling and creep-bending tests of 2024-T4 aluminum-alloy columns of slenderness ratio 111 are presented. Tests were performed at 600 degrees Fahrenheit and strain measurements were taken with high-temperature electric-resistance strain gages.
Date: May 23, 1956
Creator: Patel, Sharad A.; Kempner, Joseph; Erickson, Burton & Mobassery, Abol H.
Partner: UNT Libraries Government Documents Department

An experimental evaluation of several design variations of hollow turbine blades for expendable engine application

Description: From Summary: "An investigation was made to evaluate several design variations of hollow turbine blades intended for missile-engine use. In one general type, the airfoils were formed from sheet metal; in a second type, the blades were cast. The blades were operated in J47 engine at 7950 rpm turbine speed and 1260 degrees Fahrenheit tail-pipe temperature until a failure occurred or a service life of 30 hours had been attained."
Date: February 23, 1955
Creator: Morgan, W. C. & Kemp, R. H.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of two delta wings at Mach number 4.04 and correlations of lift and minimum-drag data for delta wings at Mach numbers from 1.62 to 6.9

Description: Report presenting tests of the aerodynamic characteristics of two delta wings of the same aspect ratio and airfoil sections at Mach number 4.04. The results indicated that the ratio of the experimental lift-curve slope to the theoretical two-dimensional lift-curve slope from previous testing is valid at this Mach number.
Date: December 23, 1952
Creator: Ulmann, Edward F. & Dunning, Robert W.
Partner: UNT Libraries Government Documents Department

Analysis of flight-determined and predicted effects of flexibility on the steady-state wing loads of the B-52 airplane

Description: From Introduction: "This paper presents the results obtained during the phase of the B-52 flight investigation concerned with the steady-state wing loads. Where possible, the effects of Mach number and flexibility on the measured load are analyzed and presented."
Date: April 23, 1958
Creator: Kuhl, Albert E.; Rogers, John T. & Little, Mary V.
Partner: UNT Libraries Government Documents Department

Airplane measurements of atmospheric turbulence for altitudes between 20,000 and 55,000 feet over the western part of the United States

Description: Report presenting a sample of data on atmospheric turbulence on Lockheed U-2 airplanes during research flights. The intensity, amount, and extent of atmospheric turbulence observed in the United States is in good agreement with data from England and Western Europe. Results regarding overall gust distribution, intensity of turbulence, percent of rough air, and size of turbulent areas are provided.
Date: August 23, 1957
Creator: Coleman, Thomas L. & Coe, Emilie C.
Partner: UNT Libraries Government Documents Department

Effect on the low-speed aerodynamic characteristics of a 49 degree sweptback wing having an aspect ratio of 3.78 of blowing air over the trailing-edge flap and aileron

Description: Report presenting an investigation in the full-scale tunnel to determine the effects on the aerodynamic characteristics of a 49.1 degree sweptback wing of blowing a high-energy stream of air over a trailing-edge flap and an aileron. The results indicated that significant increases in lift coefficient and an improvement in aileron effectiveness may be obtained by the blowing method of boundary-layer control.
Date: April 23, 1954
Creator: Whittle, Edward F., Jr. & Lipson, Stanley
Partner: UNT Libraries Government Documents Department

Effect of fuel nozzle protrusion on transient and steady-state turbojet combustor performance

Description: Report presenting the effect of small variations in the axial position of the liner with respect to the nozzle on limiting rates of change of fuel flow and steady-state combustion efficiencies in a single tubular combustor. Data were obtained with two liner configurations at three combustor-inlet conditions. Results regarding transient combustion performance and steady-state combustion performance are provided.
Date: February 23, 1955
Creator: McCafferty, Richard J. & Donlon, Richard H.
Partner: UNT Libraries Government Documents Department

Effects of taper ratio on the longitudinal characteristics at Mach numbers from 0.6 to 1.4 of a wing-body-tail combination having an unswept wing of aspect ratio 3

Description: Report presenting the results of a wind-tunnel investigation to determine the effects of a variation in wing taper ratio on the longitudinal characteristics of a wing-body combination at a variety of Mach numbers. The wings had an aspect ratio of 3, an unswept midchord line, and an NACA 64A003 profile. Results regarding the lift and pitching-moment characteristics and drag characteristics are provided.
Date: March 23, 1955
Creator: Summers, James L.; Treon, Stuart L. & Graham, Lawrence A.
Partner: UNT Libraries Government Documents Department

The effects of tip-mounted jet nacelles on the transonic characteristics of low-aspect-ratio wings

Description: Report presenting an investigation of the effects of tip-mounted jet-engine nacelles on the aerodynamic characteristics of low-aspect-ratio rectangular and tapered wings using the transonic-bump technique. The effect of the tip-mounted nacelles was generally to increase the lift-curve slopes for wings of aspect ratio 2 or larger with upper or lower mounted nacelles causing larger increases than symmetrically mounted nacelles. Results regarding rectangular wings and tapered wings are provided.
Date: December 23, 1952
Creator: Coe, Charles F.
Partner: UNT Libraries Government Documents Department

Experimental investigation of physical and combustion properties of several residual fuel oils and magnesium - fuel-oil slurries in a ram-jet-type combustor

Description: Report presenting an experimental investigation using a 1 7/8-inch diameter burner to determine the suitability of residual fuel oils as carriers in magnesium slurries. Four residual fuel oils with varying viscosities were investigated by themselves and in slurries of 50 percent magnesium. Results regarding the settling characteristics, blow-out velocity, and combustion efficiency are provided.
Date: June 23, 1953
Creator: Cook, Preston N., Jr.; Evans, Vernida E. & Lezberg, Erwin A.
Partner: UNT Libraries Government Documents Department

Experimental investigation of boundary-layer suction through slots to obtain extensive laminar boundary layers on a 15-percent-thick airfoil section at high Reynolds numbers

Description: Report presenting a wind-tunnel investigation to determine the extent to which boundary-layer removal through slots is effective as a means for maintaining extensive laminar layers at high Reynolds numbers. Results regarding drag, suction-flow and pressure-loss distribution, surface pressure distribution, lift, and some of the difficulties involved in obtaining extensive laminar flow are provided.
Date: June 23, 1952
Creator: Loftin, Laurence K., Jr. & Horton, Elmer A.
Partner: UNT Libraries Government Documents Department

Experimental investigation of creep bending and buckling of thin circular cylindrical shells

Description: From Summary: "Forty-three cylinders of 40-inch length and 16-inch diameter, made of 5052-0 aluminum-alloy sheets of 0.023-, 0.040-, 0.051-, and 0.064-inch thickness, were subjected to bending moments constant along the cylinder and in time in an oven which maintained a constant temperature of 500 degrees Fahrenheit during the test. All the cylinders failed by buckling. The time that elapsed between load application and collapse was measured."
Date: July 23, 1957
Creator: Erickson, Burton; Patel, Sharad A.; French, Francis W.; Lederman, Samuel & Hoff, N. J.
Partner: UNT Libraries Government Documents Department

Some measurements of boiling burn-out

Description: Report presenting measurements of boiling burn-out heat flux for water flowing upward through an electrically heated tube for ranges of velocity, pressure, length-diameter ratios, and subcooling.
Date: February 23, 1955
Creator: Lowdermilk, Warren H. & Weiland, Walter F.
Partner: UNT Libraries Government Documents Department