UNT Libraries Government Documents Department - 156 Matching Results

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Aerodynamic characteristics at transonic speeds of a 60 degree delta wing equipped with a constant-chord flap-type control with and without an unshielded horn balance: transonic-bump method

Description: Report presenting an investigation to determine the control hinge moments and effectiveness at transonic speeds of a delta wing equipped with a constant-chord flap-type control with and without an unshielded triangular horn balance in the 7- by 10-foot tunnel using the transonic-bump method. The data indicated that the horn balance control was consistently more effective in changing lift at all Mach numbers than was the plain control but there was no appreciable difference in pitching-moment ef… more
Date: September 16, 1952
Creator: Wiley, Harleth G. & Zontek, Leon
Item Type: Refine your search to only Report
open access

Aeronautical Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination and the Fuselage Alone Obtained in the Langley 8-Foot Transonic Tunnel

Description: Report presenting a fuselage and wing-fuselage combination with a wing of 45 degrees sweepback of the 0.25-chord line, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil sections in the slotted test section of a transonic tunnel for a range of Mach numbers and angles of attack. Results regarding lift characteristics, drag characteristics, lift-drag ratios, pitching-moment characteristics, a comparison with other test results, and base-pressure characteristics are provided.
Date: September 16, 1952
Creator: Osborne, Robert S. & Mugler, John P., Jr.
Item Type: Refine your search to only Report
open access

Altitude Cooling Investigation of the R-2800-21 Engine in the P-47G Airplane 4 - Engine Cooling-Air Pressure Distribution

Description: "A study of the data obtained in a flight investigation of an R-2800-21 engine in a P-47G airplane was made to determine the effect of the flight variables on the engine cooling-air pressure distribution. The investigation consisted of level flights at altitudes from 5000 to 35,000 feet for the normal range of engine and airplane operation. The data showed that the average engine front pressures ranged from 0.73 to 0.82 of the impact pressure (velocity head). The average engine rear pressures r… more
Date: January 16, 1947
Creator: Kaufman, Samuel J.; Staudt, Robert C. & Valerino, Michael F.
Item Type: Refine your search to only Report
open access

Altitude Investigation of Several Afterburner Configurations for the J40-WE-8 Turbojet Engine

Description: "An investigation was conducted in the Lewis altitude wind tunnel to evaluate the performance and operational characteristics of the J40-WE-8 afterburner. A brief program of minor modifications to the flame holder, diffuser, and fuel system was undertaken to improve at a burner-inlet pressure level of 620 pounds per square foot. At this pressure level, modifications to the fuel system resulted in an increase in maximum net thrust from 1500 to 1600 pounds and a reduction in specific fuel consump… more
Date: July 16, 1953
Creator: Conrad, E. William & Campbell, Carl E.
Item Type: Refine your search to only Report
open access

Altitude-wind-tunnel investigation of various can-type burners in Bumblebee 18-inch ram jet

Description: An investigation on various can-type burners in a Bumblebee 18-inch ram jet under controlled conditions of pressure altitude and ram pressure ratio was conducted in the NACA Lewis altitude wind tunnel with kerosene as fuel. The performance of the following can-type burner configurations was better than that of the other burner configurations investigated: (1) a flame holder having a two-pitch alinement of perforations, 0.07-inch-wide cooling slots, and an arrangement of fuel nozzles located wit… more
Date: March 16, 1949
Creator: Dupree, D. T.; Nussdorfer, T. J. & Sterbentz, W. H.
Item Type: Refine your search to only Report
open access

Amplitude of Supersonic Diffuser Flow Pulsations

Description: "A theoretical method for evaluating the stability characteristics and the amplitude and the frequency of pulsation of ram-jet engines without heat addition is presented herein. Experimental verification of the theoretical results are included where data were available. Theory and experiment show that the pulsation amplitude of a high mass-flow-ratio diffuser having no cone surface flow separation increases with decreasing mass flow" (p. 1).
Date: December 16, 1952
Creator: Sterbentz, William H. & Davids, Joseph
Item Type: Refine your search to only Report
open access

Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 deg wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at Mach numbers of 1.61 and 2.01 to determine the pressure distributions for a series of 20 controls on a 60 degree delta wing. Tests occurred at a range of angles of attack and control deflections. Results regarding basic pressure distributions, comparison of experimental and theoretical results, and experimental comparisons are provided.
Date: May 16, 1958
Creator: Lord, Douglas R. & Czarnecki, K. R.
Item Type: Refine your search to only Report
open access

Analysis of pressure distributions for a series of tip and trailing-edge controls on a 60 degree delta wing at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at two Mach numbers to determine the pressure distributions for a series of 20 controls on a 60 degree delta wing. Thirteen controls were of the balanced tip type and seven of the controls were of the more conventional trailing-edge type. Results regarding the basic pressure distributions, comparison of experimental and theoretical results, and some experimental comparisons are provided.
Date: May 16, 1958
Creator: Lord, Douglas R. & Czarnecki, K. R.
Item Type: Refine your search to only Report
open access

Analytical investigation of effect of water-cooled turbine blades on performance of turbine-propeller power plants

Description: "Finally the work of the report is applied exclusively to consideration of the turbine-propeller power plant because previous performance analyses of the various gas-turbine propulsion systems combine with recent improvements in propeller design indicate that it is this combination which, will give the best over-all performance in the speed ranges considered" (p. 5).
Date: August 16, 1948
Creator: Bowman, William D
Item Type: Refine your search to only Report
open access

Burning rates of single fuel drops and their application to turbojet combustion process

Description: Report presenting burning rates for single isooctane drops suspended in various quiescent oxygen-nitrogen atmospheres at room temperature and pressure. The burning rates were compared with those predicted by a previously developed theory based on a heat- and mass-transfer mechanism and with values predicted by a modification to the theory.
Date: July 16, 1953
Creator: Graves, Charles C.
Item Type: Refine your search to only Report
open access

Calibration of Air-Flow Meters for J33 Compressor Investigation

Description: Flow-metering devices used by the NACA and by the manufacturer of the J33 turbojet engine were calibrated together to determine whether an observed discrepancy in weight flow of approximately 4 percent for the two separate investigations might be due to the different devices used to meter air flow. A commercial adjustable orifice and a square-edge flat-plate orifice used by the NACA and a flow nozzle used by the manufacturer were calibrated against surveys across the throat of the nozzle. It wa… more
Date: August 16, 1948
Creator: Kovach, Karl & Withee, Joseph R., Jr.
Item Type: Refine your search to only Report
open access

Characteristics of a Hydraulic Control Determined from Transient Data Obtained with a Turbojet Engine at Altitude

Description: Memorandum presenting characteristics of a hydraulic control as determined by analyzing transient data obtained with a turbojet engine operating in the altitude wind tunnel. The excellent overall performance of the speed control is attributed to the elimination of large lags in the control system, thereby permitting the use of relatively high loop gains while still maintaining satisfactory damping in transients. Some information regarding the frequency-response analysis of speed control, simula… more
Date: June 16, 1954
Creator: Vasu, George; Hinde, William L. & Craig, R. T.
Item Type: Refine your search to only Report
open access

Combined compressor coolant injection and afterburning for turbojet thrust augmentation

Description: Report presenting a discussion of some of the requirements and of the application of the augmented performance of compressor coolant injection and afterburning in a turbojet engine in a high-speed, high-altitude flight. Results regarding the experimental performance of a combined system and the application of augmented performance to high-speed flight are provided.
Date: September 16, 1954
Creator: Useller, James W.; Huntley, S. C. & Fenn, David B.
Item Type: Refine your search to only Report
open access

Combustion-Chamber Performance Characteristics of a Python Turbine-Propeller Engine Investigated in Altitude Wind Tunnel

Description: Combustion-chamber performance characteristics of a Python turbine-propeller engine were determined from investigation of a complete engine over a range of engine speeds and shaft horsepowers at simulated altitudes. Results indicated the effect of engine operating conditions and altitude on combustion efficiency and combustion-chamber total pressure losses. Performance of this vaporizing type combustion chamber was also compared with several atomizing type combustion chambers.
Date: November 16, 1951
Creator: Campbell, Carl E.
Item Type: Refine your search to only Report
open access

Comparative Tensile Strengths at 1200 Degrees F of Various Root Designs for Cermet Turbine Blades

Description: Report presenting specimens of five different root designs, proportioned in accordance with the design surveys, and specimens of a conventional fir-tree turbine root were fabricated from a titanium carbide cement bonded with nickel. Comparative strengths were determined by short-term tensile tests at 1200 degree Fahrenheit. Results regarding blade root evaluation and rotor-segment evaluation are provided.
Date: June 16, 1953
Creator: Meyer, André J., Jr.; Kaufman, Albert & Calvert, Howard F.
Item Type: Refine your search to only Report
open access

Comparison of ignition delays of several propellant combinations obtained with modified open-cup and small-scale rocket engine apparatus

Description: From Summary: "Ignition delays of several propellant combinations obtained with a modified open-cup apparatus and with a small-scale rocket engine of approximately 50-pounds thrust were compared to study any correlations that might exist between the two methods of ignition-delay determination. The results were used in determining the relative utility of each apparatus."
Date: June 16, 1953
Creator: Ladanyi, Dezso J. & Miller, Riley O.
Item Type: Refine your search to only Report
open access

Comparison of theoretical and experimental zero-lift drag-rise characteristics of wing-body-tail combinations near the speed of sound

Description: Report presenting the zero-lift drag rise at low supersonic speeds computed by linearized theory for several wing-body-tail combinations and a comparison with experimental data. The results indicate that the computation method is capable of computing the drag rise at low supersonic speeds to an accuracy of about 20 percent.
Date: October 16, 1953
Creator: Holdaway, George H.
Item Type: Refine your search to only Report
open access

Comparison of Wind-Tunnel, Rocket, and Flight Drag Measurements for Eight Airplane Configurations at Mach Numbers Between 0.7 and 1.6

Description: Report presenting comparisons of low-lift drag measurements on eight airplane configurations at a range of Mach numbers by various techniques. Data was obtained from wind tunnel testing, rocket propelled model tests, and airplane flight tests. The agreement of data is generally good and no consistent Reynolds number effects are observed.
Date: September 16, 1954
Creator: Purser, Paul E.
Item Type: Refine your search to only Report
open access

Comparison of Wind-Tunnel, Rocket, and Flight Drag Measurements for Eight Airplane Configurations at Mach Numbers Between 0.7 and 1.6

Description: Report presenting comparisons of low-lift drag measurements on eight airplane configurations at a range of Mach numbers using various techniques. Data was obtained from wind-tunnel testing, rocket-propelled model testing, and airplane flight testing. The majority of the data showed agreement and discrepancies were likely due to issues regarding surface condition, individual test setup and accuracy, and detail geometric differences between the airplanes and respective models.
Date: September 16, 1954
Creator: Purser, Paul E.
Item Type: Refine your search to only Report
open access

Component performance investigation of L71 experimental turbine 10: effect of first-stator adjustment; internal flow conditions of J71-97 turbine with 132-percent-design stator area

Description: Report presenting an investigation of the changes in the internal flow conditions resulting from adjusting the first-stator throat area of the J71 experimental three-stage turbine. The results of interstage flow measurements obtained from a radial survey investigation conducted on the turbine when equipped with a first-stage stator with the throat area increased to 132 percent of the design area and operated at a single predetermined turbine match point are also provided.
Date: January 16, 1958
Creator: Petrash, Donald A.; Schum, Harold J. & Davison, Elmer H.
Item Type: Refine your search to only Report
open access

Criterions for prediction and control of ram-jet flow pulsations

Description: Report presenting the results of a theoretical and experimental study of ramjet diffuser flow pulsing, commonly referred to as a buzz condition, with and without combustion. The acoustical resonance properties of ram jets are an important factor in establishing the frequency of diffuser flow pulsations.
Date: May 16, 1951
Creator: Sterbentz, William H. & Evvard, John C.
Item Type: Refine your search to only Report
open access

Damping in Yaw and Static Directional Stability of a Canard Airplane Model and of Several Models Having Fuselages of Relatively Flat Cross Section

Description: Report presenting an investigation to determine the damping in yaw and static directional stability characteristics for a flat-fuselage model with its major cross-sectional axis either horizontal or vertical, for a flat-fuselage model with its major axis horizontal in combination with a 45 degree sweptback wing, and for a canard model with a triangular control surface and 45 degree sweptback wing.
Date: October 16, 1950
Creator: Johnson, Joseph L.
Item Type: Refine your search to only Report
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