UNT Libraries Government Documents Department - 130 Matching Results

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Acceleration characteristics of a turbojet engine with variable-position inlet guide vanes

Description: Report presenting a study of the acceleration characteristics of a turbojet engine equipped with variable-position inlet guide vanes in the altitude test chamber. Maximum acceleration values for 3 engines of the same model were also obtained during testing and were found to differ as much as 50 percent. Results regarding the effect of fuel step size and inlet guide vane on acceleration, effect of flight condition, reproducibility of engine acceleration, compressor pressure ratio in relation to acceleration, and acceleration with inlet air distortion are provided.
Date: July 7, 1955
Creator: Dobson, W. F. & Wallner, Lewis E.

Aerodynamic characteristics of a 0.04956-scale model of the Convair F-102B airplane at Mach numbers of 1.41, 1.61, and 2.01: COORD No. AF-231

Description: Report discussing testing of a scale model of the Convair F-102B to determine its aerodynamic characteristics at several Mach numbers. Four basic body modifications and two afterbody configurations were evaluated.The body modifications were all found to slightly reduce values of minimum drag, but did not cause a change in the static stability and lift-curve-slope values compared to the F-102A.
Date: February 7, 1956
Creator: Driver, Cornelius & Robinson, Ross B.

Analysis of V-g data obtained from several naval airplanes

Description: From Introduction: "V-g records supplied the NACA by the Bureau of Aeronautics in 1948 and 1949 have provided additional material. These records are analyzed statistically in this report to the frequency of large values of acceleration and airspeed, and results are compared with the design requirements."
Date: July 7, 1950
Creator: Thornton, James O

An Analysis of Vertical-Tail Loads Measured in Flight on a Swept-Wing Bomber Airplane

Description: From Introduction: "This paper presents results of an analysis of shear, bending-moment, and torque loads measured on the vertical tail during rudder-step, rudder-pulse, aileron-roll, and steady-sideslip maneuvers. In order to assess effects of Mach number and altitude, the maneuvers were performed at altitudes of 15,000, 25,000, and 35,000 feet and Mach numbers from 0.49 to 0.82."
Date: May 7, 1957
Creator: McGowan, William A. & Cooney, T. V.

Analytical comparison of convection-cooled turbine blade cooling-air requirements for several radial gas-temperature profiles

Description: Report presenting an analysis made to permit a comparative evaluation of the turbine rotor cooling-air requirements with convection-cooled blades for four combustor-outlet radial gas-temperature profiles: a uniform profile, a profile representable by a complete cycle of the cosine wave using cooler gas layers near the turbine casing, a profile representable by one-half cycle of the cosine wave using cooler gas layers near the stator inner ring, and an optimum profile resulting in the absolute minimum cooling-air requirements.
Date: September 7, 1955
Creator: Hubbartt, James E. & Slone, Henry O.

Average skin-friction coefficients from boundary-layer measurements in flight on a parabolic body of revolution (NACA RM-10) at supersonic speeds and at large Reynolds numbers

Description: Report presenting boundary-layer measurements on rocket-powered free-flight models to determine average skin-friction coefficients. The test body, NACA RM-10, was a fin-stabilized parabolic body of revolution of fineness ratio 12.2 with a blunt base to provide space for a rocket jet. Results regarding the skin-friction and boundary-layer profiles and experimental and theoretical curves are provided.
Date: March 7, 1951
Creator: Rumsey, Charles B. & Loposer, J. Dan

Bonded lead monoxide films as solid lubricants for temperatures up to 1250 degrees F

Description: Report presenting a friction, wear, and endurance-lift study made with bonded films of mixed oxides containing lead monoxide (PbO) as the main component. The coatings lubricated over the entire temperature range, but were far more effective from 500 to 1250 degrees Fahrenheit than at the lower temperatures. Results regarding the effect of silica additions on coating formation, determination of coating composition, effect of coating thickness on friction and wear, effect of temperature on friction and wear, and endurance properties are provided.
Date: May 7, 1957
Creator: Sliney, Harold E. & Johnson, Robert L.

The calculation of the path of a jettisonable nose section

Description: Report presenting a method for calculating the path of a jettisonable nose section at any speed by means of successive approximations using static aerodynamic characteristics. Conditions for consideration, including the effect of stabilizing fins, are included in the calculations.
Date: September 7, 1950
Creator: Goodwin, Roscoe H.

Calibration of the slotted test section of the Langley 8-foot transonic tunnel and preliminary experimental investigation of boundary-reflected disturbances

Description: Report presenting an attempt to determine the reliability and calibration of the Langley transonic tunnel in the open slotted test section. Results regarding test-section calibration, including flow uniformity, calibration, and angularity, model testing and boundary interference, and reduction of interference are provided.
Date: July 7, 1952
Creator: Ritchie, Virgil S. & Pearson, Albin O.

Combustion-efficiency and altitude-limit investigations of five fuels in an annular turbojet combustor

Description: Report presenting five fuels of boiling temperatures and several hydrocarbon types in a jet-propulsion annular combustor to determine the effect of fuel boiling temperature and paraffinic and aromatic hydrocarbon types on combustion efficiency and altitude operational limit. At the severe inlet-air condition, the highest combustion efficiencies were obtained with the paraffinic and aromatic fuels with low boiling temperatures were found to vary from 30 to 58 percent.
Date: June 7, 1954
Creator: Wear, Jerrold D. & Jonash, Edmund R.

Comparison of normal load factors experienced with jet fighter airplanes during combat operations with those of flight tests conducted by the NACA during operational training

Description: Report presenting a comparison of normal load factors measured during combat operations with those measured during an NACA flight program conducted with fully instrumented service airplanes in operational training. Results indicated that for an equal number of maneuvers, normal load factors obtained from the NACA program are greater than those obtained during combat when based on the service-limit load factor.
Date: July 7, 1954
Creator: Hamer, Harold A.; Huss, Carl R. & Mayer, John P.

Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings

Description: Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.
Date: October 7, 1953
Creator: Radin, Edward J. & Carpenter, Paul J.

Comparison of the Static Stability of a 68.7 Degree Delta-Wing Model with Dihedral and a Twisted and Cambered Wing Model of the Same Plan Form

Description: Memorandum presenting a force-test investigation to determine whether the static stability characteristics of a twisted and cambered 68.7 degree delta wing could be approximated by a plane wing of similar plan form with dihedral. Results regarding longitudinal characteristics and lateral characteristics are provided.
Date: April 7, 1955
Creator: Paulson, John W.

Correlation of supersonic convective heat-transfer coefficients from measurements of the skin temperature of a parabolic body of revolution (NACA RM-10)

Description: Report presenting local coefficients of convective heat transfer as measured from skin temperature along the body of an RM-10 NACA research missile, which consisted of a parabolic body of revolution. Results regarding recovery factors, adiabatic wall temperatures, Nusselts, Prandtl, and Reynolds numbers, and boundary-layer transition are provided.
Date: March 7, 1951
Creator: Chauvin, Leo T. & de Moraes, Carlos A.

Design and test of mixed-flow impellers 5: design procedure and performance results for two vaned diffusers tested with impeller model MFI-1B

Description: Report presenting the design procedure and experimental test results for a range of impeller speeds for two vaned diffusers of 24 and 40 vanes. Both sets of vanes were designed to give approximately the same prescribed velocity distribution on the vane surfaces and were tested with the same impeller. Results regarding overall performance and the total-pressure-loss coefficient for both vanes are provided.
Date: July 7, 1955
Creator: Hamrick, Joseph T. & Osborn, Walter M.

Determination of longitudinal stability of the Bell X-1 airplane from transient responses at Mach numbers up to 1.12 at lift coefficients of 0.3 and 0.6

Description: Report presenting an analysis of a number of free-flight transient responses resulting from small stabilizer movements obtained during testing of the Bell X-1 airplane to obtain its longitudinal stability characteristics. A comparison of flight data and model test data is also provided.
Date: November 7, 1950
Creator: Angle, Ellwyn E. & Holleman, Euclid C.

Downwash and Sidewash Fields Behind Cruciform Wings

Description: Memorandum presenting a brief account of the results of theoretical and experimental investigations of the flow fields behind lifting plane and cruciform wings. Particular attention is focused on wings of low aspect ratio.
Date: January 7, 1952
Creator: Spreiter, John R.

Dynamic Characteristics of a Single-Spool Turbojet Engine

Description: Memorandum presenting an investigation of operation of a single-spool turbojet engine with variable exhaust-nozzle area over a range of altitudes at a constant flight Mach number. Data was obtained by subjecting the engine to approximate step disturbances in the independent variables, and the information necessary to effect a linearized first-order description of the engine's dynamic operation was obtained. Results regarding rotational speed, compressor-discharge pressure, turbine-discharge pressure, net thrust, and turbine-discharge temperature are provided.
Date: August 7, 1953
Creator: Craig, R. T.; Vasu, George & Schmidt, R. D.

The effect of changes in the leading-edge radius on the aerodynamic characteristics of a symmetrical, 9-percent-thick airfoil at high-subsonic Mach numbers

Description: Report of an investigation into the effect of leading-edge radius on the high-speed aerodynamic characteristics of a symmetrical, 9-percent-thick airfoil using three different airfoils at several Mach and Reynolds numbers. Information about the normal-force coefficients, drag coefficients, moment coefficients about the quarter chord, pressure-distribution diagrams, Schileren photographs, and a comparison with data obtained in other tunnels is included.
Date: August 7, 1950
Creator: Humphreys, Milton D. & Robinson, Raymond A.