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Design and Experimental Investigation of a Single-Stage Turbine With a Rotor Entering Relative Mach Number of 2
Memorandum presenting a design and experimental investigation of a single-stage supersonic turbine. The turbine was designed for a rotor entering relative Mach number of 2. Results regarding the overall turbine performance, outer-wall static-pressure variation, momentum-loss considerations, effect of rotor modifications, and supersonic starting are provided.
Date:
September 15, 1958
Creator:
Moffitt, Thomas P.
System:
The UNT Digital Library
Investigation of Adjustable Supersonic Inlet in Combination With J34 Engine Up to Mach 2.0
Pressure recovery in adjustable supersonic inlet combined with J34 turbojet engine up to Mach 2.0.
Date:
October 15, 1954
Creator:
Nettles, J. C. & Leissler, L. A.
System:
The UNT Digital Library
Combustion-efficiency investigation of special fuels in single tubular-type combustor at simulated altitude conditions
Report presenting a combustion-efficiency investigation of 10 special straight-run distillate fuels in an individual tubular-type combustor unit of a 14-unit assembly at two simulated engine operating conditions. These distillates were obtained from various crude oils and consisted of hydrocarbon mixtures with distillations temperature varying from 93 to 690 degrees Fahrenheit. Comparison of temperature measurements obtained from two locations in the exhaust duct showed that under certain operating conditions the flame extended beyond the turbine position.
Date:
August 15, 1947
Creator:
Dittrich, Ralph T.
System:
The UNT Digital Library
Spin-Tunnel Investigation of a Model of a 60 Degree Delta-Wing Airplane to Determine the Spin, Recovery, and Longitudinal Trim Characteristics Throughout an Extensive Range of Mass Loadings
Report presenting an investigation to determine the spin, recovery, and longitudinal-trim characteristics of a 60 degree delta-wing model through an extensive range of mass loadings. Variations in the relative density, center-of-gravity position, and inertia parameters were included in testing. Results regarding the single-vertical-tail and multiple-vertical-tail configurations are provided.
Date:
February 15, 1950
Creator:
Klinar, Walter J. & Jones, Ira P., Jr.
System:
The UNT Digital Library
Experimental Investigation of a Preloaded Spring-Tab Flutter Model
"An experimental investigation was made of a preloaded spring-tab flutter model to determine the effects on flutter speed of aspect ratio, tab frequency, and preloaded spring constant. The rudder was mass-balanced, and the flutter mode studied was essentially one of three degrees of freedom (fin bending coupled with rudder and tab oscillations). Inasmuch as the spring was preloaded, the tab-spring system was a nonlinear one" (p. 1).
Date:
December 15, 1947
Creator:
Smith, N. H.; Clevenson, S. A. & Barmby, J. G.
System:
The UNT Digital Library
Evaluation of piston-type gas-generator engine for subsonic transport operation
Report presenting an evaluation of a piston-type gas-generator engine by comparing the performance of a transport airplane powered with than engine with the same airplane powered by different engines. The engines compared were a turbojet engine, a turbine-propeller engine, a compound engine, and a turbosupercharged reciprocating engine utilizing a variable-area exhaust jet nozzle. Results regarding optimum altitude and transport performance are provided.
Date:
July 15, 1949
Creator:
Lietzke, A. F. & Henneberry, Hugh M.
System:
The UNT Digital Library
Experimental Investigation of Various Wing-Mounted External Stores on a Wing-Fuselage Combination Having a Sweptback Wing of Inverse Taper Ratio
Report presenting an investigation in the high speed tunnel to determine the effects of several wing-mounted external-store configurations on the aerodynamic characteristics of a model of a swept wing-fuselage combination for a range of Mach numbers. Some of the configurations explored included inboard underwing installations and wing-tip installations. Results regarding lift-drag ratios, drag characteristics, lift-curve slope, and pitching-moment characteristics are provided.
Date:
September 15, 1950
Creator:
Spreemann, Kenneth P. & Silvers, H. Norman
System:
The UNT Digital Library
Altitude-Wind-Tunnel Investigation of Combustion-Chamber Performance on J47 Turbojet Engine
From Introduction: "Results are presented to indicate the effect of altitude, flight Mach number, and exhaust-nozzle-outlet area on the combustion efficiency, the losses in total pressure occurring in the combustion chamber, and the fractional loss in engine cycle efficiency resulting from combustion-chamber pressure losses. The engine cycle efficiency is also presented.These results are shown graphically as a fraction of corrected engine speed and in tabular form."
Date:
December 15, 1950
Creator:
Campbell, Carl E.
System:
The UNT Digital Library
Experimental performance of chlorine trifluoride-hydrazine propellant combination in 100-pound-thrust rocket engine
Report presenting an investigation of the experimental performance of chlorine triflouride and hydrazine measured over a range of propellant mixtures in a 100-pound-thrust rocket engine. Experimental values of specific impulse, volume specific impulse, heat rejection per propellant weight, nozzle thrust coefficient, and characteristic velocity were obtained as functions of percent fuel by weight in the propellant mixture.
Date:
August 15, 1949
Creator:
Ordin, Paul M. & Miller, Riley O.
System:
The UNT Digital Library
Comparison of Effectiveness of Coordinated Turns and Level Sideslips for Correcting Lateral Displacement During Landing Approaches
Memorandum presenting a calculation of the amount of possible correction for coordinated turns with limited bank angle and level sideslips for a large transport airplane, the C-54D. The results indicate that for all instances from the end of the runway, coordinated turns are the more effective maneuver.
Date:
December 15, 1949
Creator:
Faber, Stanley
System:
The UNT Digital Library
Flow studies in the asymmetric adjustable nozzle of the Ames 6-by 6-foot supersonic wind tunnel
Report presenting surveys of the flow of the asymmetric adjustable nozzle of the 6- by 6-foot supersonic wind tunnel, which were made to determine the uniformity of the air stream. Test techniques for minimizing the effects of stream irregularities and the results of force and pressure-distribution tests of a swept-wing model are presented to illustrate the effectiveness of these techniques.
Date:
September 15, 1949
Creator:
Frick, Charles W. & Olson, Robert N.
System:
The UNT Digital Library
Calculation of Aerodynamic Forces on a Propeller in Pitch or Yaw
Report presenting an analysis to determine the applicability of existing propeller theory and the theory of oscillating airfoils to the problem of determining the magnitude of the forces on propellers in pitch or yaw. The steady-state method for calculating propeller forces appears to give satisfactory results.
Date:
February 15, 1949
Creator:
Crigler, John L. & Gilman, Jean, Jr.
System:
The UNT Digital Library
A Summary Report on the Effects of Mach Number on the Span Load Distribution on Wings of Several Models
Memorandum presenting an investigation of the change in spanwise load distribution at high Mach numbers, which is of considerable interest because lateral movement of the center of lift affects the trim, stability, and structural factors of safety of an airplane. The data is not sufficient to permit isolation of the effects of changes in wing configuration, but in a majority of cases, the tests reveal a tendency for the center of lift to shift outboard with increasing Mach number.
Date:
July 15, 1947
Creator:
Jessen, Henry, Jr.
System:
The UNT Digital Library
Aerodynamic Study of a Wing-Fuselage Combination Employing a Wing Swept Back 63 Degrees: Characteristics Throughout the Subsonic Speed Range With the Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25
Report presenting wind-tunnel testing to determine the independent effects of Mach and Reynolds numbers on the aerodynamic characteristics of a wing-fuselage combination with a wing with the leading edge swept back 63 degrees and with camber and twist. Results regarding the fuselage alone and the effects of camber and twist are also provided.
Date:
August 15, 1949
Creator:
Jones, J. Lloyd & Demele, Fred A.
System:
The UNT Digital Library
Analysis of the Effects of Various Mass, Aerodynamic, and Dimensional Parameters on the Dynamic Lateral Stability of the Douglas D-558-2 Airplane
Report presenting an investigation of the effects of various mass, aerodynamic, and dimensional parameters on the dynamic lateral stability of the Douglas D-558-2 airplane. Results regarding an airplane with the flaps and gear retracted, airplane at sea level with flaps deflected 50 degrees and landing gear lowered, and effect of assumed modifications to airplane are provided.
Date:
April 15, 1949
Creator:
Queijo, M. J. & Michael, W. H., Jr.
System:
The UNT Digital Library
Experimental investigation at supersonic speeds of twin-scoop duct inlets of equal area 4: some effects of internal duct shape upon an inlet enclosing 37.2 percent of the forebody circumference
Report presenting tests to determine the recovery of total pressure attainable at a range of Mach numbers, which were performed with models with twin-scoop inlets situated on the sides of a long forebody. Results regarding ducts without slots and ducts with slots are provided.
Date:
March 15, 1949
Creator:
Davis, Wallace F.; Edwards, Sherman S. & Brajnikoff, George B.
System:
The UNT Digital Library
Reynolds number effect on axial-flow compressor performance
Investigation conducted in the altitude wind tunnel to study the effect of Reynolds number on the performance of an axial-flow compressor. The compressor was operated as a part of a turbojet engine over a range of pressure altitudes and compressor-inlet Reynolds numbers. Results regarding compressor efficiency, air flow, and a comparison with axial-flow compressors of different design are provided.
Date:
September 15, 1949
Creator:
Wallner, Lewis E. & Fleming, William A.
System:
The UNT Digital Library
Summary of the Availability and Performance Problems of High Octane Number Fuels
Memorandum presenting a study to determine the possible blending agents or additives that may be used to supplement current high performance number, rich rating components in future aviation fuels. The study indicated that such high rich rating blending agents as toluene and xylene cannot be made available in sufficient quantities to maintain the rich rating performance of the fuels when reducing the lead content from 4.6 to 3.0 ml per gallon.
Date:
April 15, 1949
Creator:
NACA Committee on Aircraft Fuels
System:
The UNT Digital Library
Altitude-wind-tunnel investigation of thrust augmentation of a turbojet engine IV: performance with tail-pipe burning and water injection
From Introduction: "Thrust augmentation of an axial-flow-type turbojet engine by burning fuel in the tail pipe is discussed in references 1 to 3. Thrust augmentation of the same turbojet engine by water injection at the compressor inlet is reported in reference 4."
Date:
June 15, 1948
Creator:
Dietz, Robert O., Jr.; Wishnek, George & Kuenzig, John K.
System:
The UNT Digital Library
A comparison of two submerged inlets at subsonic and transonic speeds
Report presenting an investigation of the operation of two submerged-type inlets in a wind tunnel at subsonic and transonic speeds. The pressure recovery was relatively constant throughout the lower subsonic speed range. The ability of the divergent-walled inlet to operate with satisfactory pressure recovery at higher free-stream Mach numbers than was possible with the parallel-walled inlet is attributed to the difference in the boundary-layer characteristics of the two types of inlets.
Date:
September 15, 1949
Creator:
Mossman, Emmet A.
System:
The UNT Digital Library
Investigation of a Shrouded and an Unshrouded Axial-Flow Supersonic Compressor
Report discussing tests of an unshrouded axial-flow supersonic compressor rotor. Information about the pressure ratio, efficiency, and flow rate with and without inlet guide vanes is provided. The results are also compared to testing on the original shrouded rotor.
Date:
September 15, 1950
Creator:
Boxer, Emanuel & Erwin, John R.
System:
The UNT Digital Library
Preliminary investigation of molybdenum disulfide-air-mist lubrication for roller bearings operating to DN values of 1 x 10(exp 6) and ball bearings operating to temperatures of 1000 degrees F
The effectiveness of molybdenum disulfide MoS2 as a bearing lubricant was determined at high temperature and at high speeds. A 1-inch-bore ball bearing operated at temperatures to 1000 F, a speed of 1725 rpm, and a thrust load of 20 pounds when lubricated only with MoS2-air mist. A 75-millimeter-bore cageless roller bearing, provided with a MoS2-syrup coating before operation, operated at DN values to 1 x 10(exp 6) with a load of 368 pounds.
Date:
October 15, 1951
Creator:
Macks, E. F.; Nemeth, Z. N. & Anderson, W. J.
System:
The UNT Digital Library
Flight Investigation at Mach Numbers From 0.8 to 1.5 of the Drag of a Canopy Located at Two Positions on a Parabolic Body of Revolution
Report presenting the results of a free-flight investigation of two drag research models equipped with canopies for a range of Mach numbers from 0.8 to 1.5. The main difference between the models was the location of the canopy, which was at the 15-percent fuselage station on one model and the 25-percent fuselage station on the other. The additional drag due to the canopies was about 10 to 20 percent of the total configuration drag at supersonic speeds.
Date:
March 15, 1951
Creator:
Welsh, Clement J. & Morrow, John D.
System:
The UNT Digital Library
Skin-Temperature Telemeter for Determining Boundary-Layer Heat-Transfer Coefficients
Memorandum presenting a description of a method of telemetering skin temperature using a small resistance wire pickup with a time constant of less than 0.003 second to determine boundary-layer heat-transfer coefficients. An evaluation of the accuracy of the method of measuring the heat-transfer coefficient is given for a particular application.
Date:
March 15, 1951
Creator:
Fricke, Clifford L. & Smith, Francis B.
System:
The UNT Digital Library