UNT Libraries Government Documents Department - 156 Matching Results

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Low-Speed Investigation of a 0.16 Scale Model of the X-3 Airplane: Lateral and Directional Characteristics

Description: Memorandum presenting a wind-tunnel investigation of the low-speed, static, lateral and directional characteristics of a model of an early design of the X-3 airplane with the wing flaps neutral and deflected. The model utilized a wing with an aspect ratio of 3.01, a 4.5-percent-thick hexagonal section, and a taper ratio of 0.4. Results regarding lateral stability and control with the flaps neutral, with the flaps fully deflected, with miscellaneous additions to the complete model, directional s… more
Date: March 16, 1951
Creator: Delaney, Noel K. & Hayter, Nora-Lee F.
Item Type: Refine your search to only Report
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Low-Speed Investigation of the Aerodynamic Loads on the Droop-Nose Flap of a Wing With Leading Edge Swept Back 47.5 Degrees and Having Symmetrical Circular-Arc Airfoil Sections at a Reynolds Number of 4.3 X 10 (Exp 6)

Description: Report presenting an investigation of the pressure distribution on the full-span droop-nose flap of a wing with the leading edge swept back 47.5 degrees and symmetrical circular-arc airfoil sections. Flap pressure distributions were obtained for the base configuration and various deflections of the full-span droop-nose flap and other flap deflection combinations. Information regarding the flow and section characteristics, spanwise loading parameters, center-of-pressure variation, and flap norma… more
Date: January 16, 1950
Creator: Whittle, Edward F., Jr. & Fink, Marvin P.
Item Type: Refine your search to only Report
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Low-speed tests of a model simulating the phenomenon of control-surface buzz

Description: Report presenting low-speed tests of an airfoil model with a freely hinged flap attached to spoilers which passed through slots in the airfoil ahead of the hinge line. Testing indicated that buzz is not caused simply by buffeting of a flap by separated flow. Results regarding the oscillations experienced with the spoiler and flap in several positions are provided.
Date: August 16, 1950
Creator: Phillips, William H. & Adams, James J.
Item Type: Refine your search to only Report
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Matching of Auxiliary Inlets to Secondary-Air Requirements of Aircraft Ejector Exhaust Nozzles

Description: Report presenting an analysis of the problems associated with matching secondary-air requirements of ejector exhaust nozzles and auxiliary inlets has been made for free-stream Mach numbers up to 2.0. The analysis indicated that inlets located in the free stream supply higher pressure recovery than ejectors generally require for optimum net internal thrust at Mach numbers above about 1.4. Net-thrust gains can be achieved by immersing the auxiliary inlet in a boundary layer where the inlet-moment… more
Date: August 16, 1955
Creator: Hearth, Donald P.; Englert, Gerald W. & Kowalski, Kenneth L.
Item Type: Refine your search to only Report
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Measurements of the Drag and Pressure Distribution on a Body of Revolution Throughout Transition From Subsonic to Supersonic Speeds

Description: Memorandum presenting an investigation of the drag and pressure distribution on a body of revolution of fineness ratio 12 as measured by the free-fall method. Analysis of the results has provided knowledge of the mechanism of the abrupt drag rise which occurs near the speed of sound, and demonstrates that the theoretical method described in a previous report satisfactorily predicts the shape of the measured pressure distributions at low supersonic speeds.
Date: January 16, 1950
Creator: Thompson, Jim Rogers
Item Type: Refine your search to only Report
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[Memorandums on the Subject of D-558 Airplane]

Description: "An investigation of the air-stream fluctuations at the tail of the D-558-1 airplane has been made at high speed for the purpose of determining the vertical region in which the horizontal tail may be placed without becoming subject to tail buffeting. The investigation was made for a range of Mach numbers from 0.775 to 0.907, and a range of vertical positions at the tall to include two proposed horizontal-tail positions. The tests were made at two angles of attack, 0,2 deg. and 4.2 deg., represe… more
Date: January 16, 1947
Creator: Pendley, Robert E.
Item Type: Refine your search to only Report
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A Method for Estimating the Components of Lift of Wing-Body Combinations at Supersonic Speeds

Description: Report presenting the lift of wing-body combinations at supersonic speeds as obtained by means of an approximate linearized-theory analysis involving an assumption concerning the geometry of the body. A comparison with several groups of data is provided to show the accuracy of the method.
Date: September 16, 1952
Creator: Tucker, Warren A.
Item Type: Refine your search to only Report
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NACA Investigation of Fuels Corresponding to Specification an-F-58 : Results of Studies in Single Combustors of J-33, J-34, J-35, and Nene Turbojet Engines

Description: "The NACA is engaged in a program to evaluate the performance of fuels conforming to AN-F-58 specification in both full-scale engines and single combustors. This research memorandum constitutes an interim report on the results obtained on single cosibustors" (p. 1).
Date: November 16, 1945
Creator: Cleveland Laboratory Staff
Item Type: Refine your search to only Report
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An NACA Vane-Type Angle-of-Attack Indicator for use at Subsonic and Supersonic Speeds

Description: A vane-type angle-of-attack indicator suitable for measurements at both subsonic and supersonic speeds has been developed by the National Advisory Committee for Aeronautics. A brief history is given of the development, and a wind-tunnel calibration of the indicator is presented, together with a discussion of the corrections to be applied to the indicated readings.
Date: August 16, 1949
Creator: Mitchell, Jesse L. & Peck, Robert F.
Item Type: Refine your search to only Report
open access

Note on some observed effects of rocket motor operation on the base pressures of bodies in free light

Description: Some measurements of the effects of rocket-motor operation on base pressure were obtained incidental to other research on some bodies in free flight. These data are presented and qualitatively analyzed. The analysis indicates that jet effects on drag are of sufficient importance to deserve consideration in the design of jet motor nozzles, especially for aircraft and missiles where the thrust and drag are of the same order of magnitude. The base-pressure changes induced by the jet should be cons… more
Date: November 16, 1950
Creator: Purser, Paul E.; Thibodaux, Joseph G. & Jackson, H. Herbert
Item Type: Refine your search to only Report
open access

Notes on low-lift buffeting and wing dropping at Mach numbers near 1

Description: From Summary: "A study of the available transonic Mach number data on low-lift buffeting, wing dropping, and changes in the angles of zero lift for symmetrical airfoils indicates that these phenomena are allied and are probably the result of shock-induced separation. The study has indicated that there are combinations of airfoil-thickness ratio, aspect ratio, and sweep which may allow flight through the transonic speed range without experiencing buffet or wing drop at low lift."
Date: March 16, 1951
Creator: Purser, Paul E.
Item Type: Refine your search to only Report
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Notes on the prediction of shock-induced boundary-layer separation

Description: The present status of available information relative to the prediction of shock-induced boundary-layer separation is discussed. Experimental results showing the effects of Reynolds number and Mach number on the separation of both laminar and turbulent boundary layer are given and compared with available methods for predicting separation. The flow phenomena associated with separation caused by forward-facing steps, wedges, and incident shock waves are discussed. Applications of the flat-plate da… more
Date: September 16, 1953
Creator: Lange, Roy H.
Item Type: Refine your search to only Report
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Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 1: two-dimensional compression-ramp inlets with semicircular cowls

Description: Report presenting an experimental investigation to determine the performance of twin-scoop side inlets located on the fuselage of a proposed aircraft in a region of large boundary-layer thickness. Inlet configurations with subsonic and supersonic cowlings which utilized two-dimensional compression ramps and ram-type scoops for boundary-layer-removal systems were investigated at several Mach number ranges. Results regarding supersonic Mach number range, angle of attack, subsonic Mach number, and… more
Date: July 16, 1952
Creator: Valerino, Alfred S.
Item Type: Refine your search to only Report
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Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 3: normal wedge inlet with semicircular cowl

Description: Report presenting an investigation of inlets utilizing two-dimensional compression wedges mounted normal to the fuselage surface with ram-type scoops for partial removal of the boundary layer. Two compression-wedge angles were included to simulate fixed positions of a variable-geometry configuration. Results regarding supersonic performance characteristics and subsonic and take-off performance characteristics are provided.
Date: October 16, 1952
Creator: Esenwein, Fred T.
Item Type: Refine your search to only Report
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Performance Investigation of a Jumo 004 Combustor

Description: Report presenting an investigation of a German Jumo 004 combustor under conditions simulating zero-ram operation of a 24C jet-propulsion engine over ranges of altitude and engine speed to obtain the altitude operating limits and characteristics. Combustion efficiency, outlet-temperature distribution, and total-pressure drop were determined. The performance of the combustor with 62-octane and JP-1 fuels were also compared.
Date: July 16, 1947
Creator: Miller, Robert C.
Item Type: Refine your search to only Report
open access

Performance investigation of can-type combustor 1: instrumentation, altitude operational limits and combustion efficiency

Description: Report presenting an investigation of the performance of a single can-type combustor designed for a turbojet engine equipped with an 11-stage axial-flow compressor and a single-stage turbine. The investigation was conducted to determine the altitude operational limits of the engine for two fuels, combustion efficiencies at various simulated conditions of altitude and engine speed, combustor-outlet temperature distribution for several altitudes at constant engine speed, and combustor total-press… more
Date: September 16, 1948
Creator: Cook, William P. & Zettle, Eugene V.
Item Type: Refine your search to only Report
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Performance of a vaporizing annular turbojet combustor at simulated high altitudes

Description: Report presenting an experimental vaporizing annular combustor that evolved from a high-performance annular combustor developed for vapor-fuel injection. The combustor consisted of a one-quarter sector of a single-annulus combustor designed to fit in a housing with an outside diameter of 25.5 inches, an inside diameter of 10.6 inches, and a combustor length of approximate 23 inches. Results regarding the performance of the Model 29I combustor, performance of Model 30, and performance of the bes… more
Date: September 16, 1954
Creator: Norgren, Carl T.
Item Type: Refine your search to only Report
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Performance of air inlets at transonic and low supersonic speeds

Description: A general discussion of the air-inlet problem is presented. Recently obtained drag and pressure-recovery data for transonic-type nose, scoop, and wing-root inlets are summarized. Preliminary results concerning the performance of the sharp-edged supersonic-type inlets at transonic and subsonic speeds also are given.
Date: February 16, 1952
Creator: Nichols, Mark R. & Pendley, Robert E.
Item Type: Refine your search to only Report
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Performance of an experimental annular turbojet combustor with methane and propane

Description: Combustion efficiencies obtained with gaseous methane were compared with reported data obtained with gaseous propane for the same experimental combustor configuration. The combustion efficiencies obtained with methane were 98, 91, and 77 percent at simulated flight altitudes of 56,000, 70,000 and 80,000 feet, corresponding to combustor inlet-air pressures from 15 to 5 inches of mercury absolute. Combustion efficiencies with propane were equivalent to those with methane up to a simulated altitud… more
Date: January 16, 1957
Creator: Norgren, Carl T.
Item Type: Refine your search to only Report
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Performance of Inconel 550 Turbine Blades in a Turbojet Engine and Effects of Different Forging Temperatures and Heat Treatments

Description: Report presenting an investigation to determine the effects of forging at 1950 degrees and 2150 degrees Fahrenheit as well as the effects of several heat treatments on the performance of Inconel 550 in a turbojet engine. Differences in engine performance of the different turbine blades could not be associated with consistent differences in microstructure or grain size. Results regarding blade performance, blade elongation during engine operation, microstructure of as-heat-treated blades, grain … more
Date: August 16, 1955
Creator: Gyorgak, C. A.; Johnston, J. R. & Weeton, J. W.
Item Type: Refine your search to only Report
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Performance of mixed-flow impeller, model MFI-1B, with diffuser vanes at equivalent impeller speeds from 1100 to 1700 feet per second

Description: Report presenting an investigation of the performance characteristics of a mixed-flow impeller (Model MFI-1B) in combination with a vaned diffuser. The results indicated that the peak pressure ratio and maximum efficiency were not being obtained at overdesign speeds because of premature surge. Increasing inlet angle at the leading edge of the vanes improved the pressure ratio and efficiency at overdesign speeds with little to no effect on underdesign speeds.
Date: June 16, 1954
Creator: Osborn, Walter M.
Item Type: Refine your search to only Report
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Preliminary Aerodynamic Investigation of the Effect of Camber on a 60 Degree Delta Wing with Round and Beveled Leading Edges

Description: Memorandum presenting an exploratory investigation to determine the aerodynamic effects of camber on a 60 degree apex delta-wing model conducted in the 300 mph 7- by 10-foot tunnel. Camber variation was accomplished through the deflection of full-span round and 25 degree beveled leading-edge flaps on a flat-sided triangular plan-form wing.
Date: August 16, 1949
Creator: Riebe, John M. & Fikes, Joseph E.
Item Type: Refine your search to only Report
open access

Preliminary Analysis of Performance of Turbojet Engines Used as Pumps for Boundary-Layer Control

Description: Memorandum presenting a determination of the effects on engine performance of using turbojet engines for boundary-layer control by suction at the engine inlet or by bleeding air from the compressor outlet for three current production engines. Results regarding bleed, suction, and variable-area turbine are provided.
Date: August 16, 1955
Creator: Conrad, E. William
Item Type: Refine your search to only Report
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Preliminary drag and heat-transfer data obtained from air-launched cone-cylinder test vehicle over Mach number range from 1.5 to 5.18

Description: From Summary: "An air-launched cone-cylinder test vehicle designed to obtain data at Mach numbers above 4.0 was rocket boosted from a release Mach number of 5.18. The vehicle was launched at an altitude of 35,000 feet and reached peak velocity of 5150 feet per second at 28,500 feet. The total-drag coefficient (based on maximum cross-sectional area) decreased gradually from 0.31 at a Mach number of 1.75 to 0.145 at a Mach number of 5.18, while the Reynold's number (based on body length) increase… more
Date: November 16, 1953
Creator: Messing, Wesley E.; Rabb, Leonard & Disher, John H.
Item Type: Refine your search to only Report
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