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Investigation of shock diffusers at Mach number 1.85 2: projecting double-shock cones
Report presenting an investigation in the 18- by 18-inch supersonic tunnel to determine the total-pressure recovery obtainable at Mach number 1.85 with a shock diffuser with projective cones designed to produce two oblique shocks ahead of the diffuser inlet. The variation of total-pressure recovery with tip projection was investigated for four cones with different included angles. A maximum total-pressure recovery of 94.5 percent was attained with the best configuration at an angle of 0 degrees.
Date:
June 17, 1947
Creator:
Moeckel, W. E.; Connors, J. F. & Schroeder, A. H.
System:
The UNT Digital Library
Measurements of the effects of thickness ratio and aspect ratio on the drag of rectangular-plan-form airfoils at transonic speeds
Report presenting testing conducted on two airfoils from a series of rectangular-plan-form airfoils of aspect ratios 7.6 and 5.1 and with NACA 65-006, 65-009, and 65-012 sections using the free-fall method. Results regarding the time histories, ground-velocity data, airfoil drag measurements, and drag coefficients are provided.
Date:
June 20, 1947
Creator:
Thompson, Jim Rogers & Mathews, Charles W.
System:
The UNT Digital Library
Numerical solution of equations for one-dimensional gas flow in rotating coolant passages
Report presenting a theoretical analysis of the air flow through the blade coolant passages in an air-cooled turbine rotor. The simultaneous effects of area change, compressibility, wall friction, heat transfer, and rotation were included.
Date:
June 26, 1950
Creator:
Brown, W. Byron & Rossbach, Richard J.
System:
The UNT Digital Library
Supplementary analysis of the dynamic lateral stability characteristics of the Bell X-2 airplane as affected by variations in mass and aerodynamic parameters
Report presenting the application of an estimation of the derivative of yawing moment due to rolling to the dynamic lateral stability characteristics of the Bell X-2. Results regarding the airplane with flaps and gear retracted and airplane with flaps and gear lowered are provided.
Date:
June 26, 1950
Creator:
Michael, William H., Jr. & Queijo, M. J.
System:
The UNT Digital Library
An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback: Static longitudinal stability and control characteristics at a Mach number of 1.59
Report presenting an investigation in the 4- by 4-foot supersonic tunnel to determine the static longitudinal stability and control characteristics of a supersonic aircraft configuration at a Mach number of 1.59. The model had a 40 degree sweptback tapered wing with 10-percent-thick circular-arc sections normal to the quarter-chord line.
Date:
June 29, 1950
Creator:
Spearman, M. Leroy & Hilton, John H., Jr.
System:
The UNT Digital Library
Heat-transfer and operating characteristics of aluminum forced-convection and stainless-steel natural-convection water-cooled single-stage turbines
Report presenting testing of two water-cooled turbines, one of aluminum alloy using forced-convection cooling and one of stainless steel using natural-convection cooling, to obtain heat-transfer and general operating data like blade temperatures, coolant-flow rates, and coolant pumping losses. Results regarding outside and inside heat-transfer results, coolant pumping power, general operating results, and practical considerations for both are provided.
Date:
June 30, 1950
Creator:
Freche, John C. & Diaguila, A. J.
System:
The UNT Digital Library
Effect of Compressibility and Camber as Determined From an Investigation of the NACA 4-(3)(08)-03 and 4-(5)(08)-03 Two-Blade Propellers Up to Forward Mach Numbers of 0.925
Report presenting testing of two NACA two-blade propellers at a range of blade angles and Mach numbers. The effect of compressibility and design section camber are presented for each propeller. The results indicated that if the outboard sections of a propeller are the thinnest, the design of the propellers should incorporate loading distribution that is concentrated in the tip sections.
Date:
June 29, 1950
Creator:
Carmel, Melvin M.; Morgan, Francis G., Jr. & Coppolino, Domenic A.
System:
The UNT Digital Library
Investigation of combustion in 16-inch ram jet under simulated conditions of high altitude and high Mach number
Results obtained with three different burner configurations in a connected-pipe investigation of a 16-inch ram jet are presented. The radial position of the fuel injector and the engine-outlet area both affected burner performance. For a given configuration, only slight changes in total-pressure ratio across the combustion chamber were obtained over the complete range of operation. With one burner, combustion efficiencies obtained at a combustion-chamber-inlet static pressure of 800 pounds per square foot absolute were greater than those obtained at 1920 pounds per square foot absolute.
Date:
June 27, 1957
Creator:
Nussdorfer, T. J.; Sederstrom, D. C. & Perchonok, E.
System:
The UNT Digital Library
Preliminary Investigation of the Transonic Characteristics of an NACA Submerged Inlet
Report presenting an investigation of an NACA submerged inlet operating over a range of mass-flow ratios and oncoming flow angles through a range of Mach numbers by use of a transonic bump. Results regarding the ram-recovery ratio, pressure distributions, and tuft studies are provided.
Date:
June 5, 1950
Creator:
Axelson, John A. & Taylor, Robert A.
System:
The UNT Digital Library
Low-speed investigation of leading-edge and trailing-edge flaps on a 47.5 degree sweptback wing of aspect ratio 3.4 at a Reynolds number of 4.4 x 10(exp 6)
Report presenting an investigation in the full-scale tunnel of the low-speed longitudinal characteristics of a 47.5 degree sweptback wing-fuselage combination with various extensible leading-edge-flap and plain trailing-edge-flap arrangements. Results regarding the basic longitudinal characteristics, extensible leading-edge flaps, plain trailing-edge flaps, and flap combinations are provided.
Date:
June 12, 1950
Creator:
Pasamanick, Jerome & Sellers, Thomas B.
System:
The UNT Digital Library
A fuel-distribution control for gas-turbine engines
"The principle of operation of a device to control the distribution of fuel to any number of discharge nozzles of a gas-turbine engine is presented. A description of an experimental model of the device and the results of a bench investigation are presented. This device controlled the flow to four discharge nozzles within 2 percent of perfect distribution over a wide range of fuel flow and was unaffected by uneven discharge-nozzle pressures" (p. 1).
Date:
June 14, 1948
Creator:
Gold, Harold & Straight, David M.
System:
The UNT Digital Library
High-Speed Wind-Tunnel Investigation of a Flying-Boat Hull With High Length-Beam Ratio
Report presenting the results of an investigation to determine the effect of Mach number on the aerodynamic characteristics of a flying-boat hull with a high length-beam ratio. Information about the drag coefficients, angles of attack for minimum drag, and longitudinal and directional stability is provided.
Date:
June 30, 1948
Creator:
Riebe, John M. & Naeseth, Rodger L.
System:
The UNT Digital Library
Initial Flight Test of the NACA FR-1-A, a Low-Acceleration Rocket-Propelled Vehicle for Transonic Flutter Research
Report presenting testing on the first of a series of flutter rockets, designated the NACA FR-1-A, which was tested with two identical swept wings. Results regarding the launching, flight, and wing failure are provided.
Date:
June 29, 1948
Creator:
Angle, Ellwyn E.
System:
The UNT Digital Library
Investigation of Effects of Several Fuel-Injection Locations on Operational Performance of a 20-Inch Ram Jet
Report presenting the results of an investigation to determine the effects of several methods of fuel injection on the operational performance of a 20-inch ram jet. Four fuel-injection arrangements using the same flame holder were presented. Results regarding the variation of combustion efficiency, ram-pressure ratio, location of the point of fuel injection, and range of fuel-air ratios over which combustion can be maintained are provided.
Date:
June 8, 1948
Creator:
Sterbentz, W. H.; Perchonok, E. & Wilcox, F. A.
System:
The UNT Digital Library
Preliminary full-scale investigation of a 1/3-scale model of a convertible-type airplane
Report presenting the results of a preliminary investigation of a scale model of a convertible-type airplane in the full-scale tunnel. The maximum lift and stalling characteristics of several configurations, the longitudinal stability characteristics, and the effectiveness of the control surfaces with the propellers removed are provided. Results regarding the propulsive characteristics, and effect of propeller operation on the lift and static thrust of the model propellers are also provided.
Date:
June 7, 1949
Creator:
Lange, Roy H.; Cocke, Bennie W., Jr. & Proterra, Anthony J.
System:
The UNT Digital Library
Comparison of Hovering Performance of Helicopters Powered by Jet-Propulsion and Reciprocating Engines
Report presenting an investigation of the maximum hovering time, or the time that a helicopter can sustain itself without motion, for helicopters using a reciprocating engine, by ramjet engines at the tips of rotor blades, and by pulse-jet engines at the tips of rotor blades. Testing showed that the reciprocating engine permitted much longer hovering time than the jet-propulsion engines, but the jet-propulsion engines were much lighter and could lift greater disposable loads.
Date:
June 11, 1948
Creator:
Brightwell, Virginia L.; Peters, Max D. & Sanders, J. C.
System:
The UNT Digital Library
Comparison of performance of AN-F-58 and AN-F-32 fuels in J33-A-23 turbojet engine
Report presenting an investigation using a 4600 pound-thrust turbojet engine as part of a program to determine the comparative performance of fuels conforming to specifications AN-F-58 and AN-F-32. Results regarding the altitude performance, altitude low-speed blow-out limits, idling limits of fuel-metering control, altitude windmilling starts, carbon-deposition rates, and iron oxide contamination are provided.
Date:
June 2, 1949
Creator:
Wilsted, H. D. & Armstrong, J. C.
System:
The UNT Digital Library
General Treatment of Compressible Flow in Ejectors and Example of Its Application to Problem of Effect of Ejector Addition on Thrust of Jet-Propulsion Units
Memorandum presenting a general treatment of compressible flow in ejectors with friction in the mixing tube included. A secondary object is to show the application of the flow theory to the calculation of the effect of ejector addition on thrust of jet-propelled airplanes and missiles. Results regarding the outline of methods of applying the general theory to some other problems and future explorations of ejector problems are provided.
Date:
June 16, 1947
Creator:
Ellerbrock, Herman H., Jr.
System:
The UNT Digital Library
Measurements of Aileron Effectiveness of Bell X-1 Airplane Up to a Mach Number of 0.82
"Abrupt, rudder-fixed aileron rolls have been made with the Bell X-1 airplane having a 10-percent-thick wing in glides to a Mach number of 0.82 at about 30,000 feet pressure altitude. Aileron movements were between one-fourth and one-half of full deflection. These aileron rolls indicate that Mach number has little effect on the aileron effectiveness up to a Mach number of 0.82" (p. 1).
Date:
June 20, 1949
Creator:
Drake, Hubert M.
System:
The UNT Digital Library
Wind-tunnel investigation of transonic aileron flutter
Report presenting a partial-span wing tested to determine the cause of a flutter which had occurred in high-speed flight. Changes were made to the wing stiffness, location of the center of gravity of the wing, and the mass balance of the aileron. Results regarding the effect of wing changes on flutter, effect of aileron changes on flutter, shock-wave study, and static aerodynamic coefficients are provided.
Date:
June 9, 1949
Creator:
Erickson, Albert L. & Mannes, Robert L.
System:
The UNT Digital Library
Estimated transonic flying qualities of a tailless airplane based on a model investigation
Report presenting an analysis of the estimated flying qualities of a tailless airplane with the wing quarter-chord line swept back 35 degrees in a range of Mach numbers based on tests of a model of the airplane in the 7- by 10-foot tunnel. Results regarding performance, longitudinal stability and control, and lateral stability and control are provided.
Date:
June 8, 1949
Creator:
Donlan, Charles J. & Kuhn, Richard E.
System:
The UNT Digital Library
Flight Investigation of the Jettisonable-Nose Method of Pilot Escape Using Rocket-Propelled Models
Report discussing testing using two rocket-propelled models to test the jettisonable-nose method of pilot escape. The nose was jettisoned successfully on the second attempt and the accelerations produced were found to be within human tolerance. The first test ended with a collision of the nose and wing, indicating that this is a possible risk during power-on flight.
Date:
June 2, 1949
Creator:
Lundstrom, Reginald R. & O'Kelly, Burke R.
System:
The UNT Digital Library
Carbon deposition from AN-F-58 fuels in a J33 single combustor
Report presenting an investigation using a single combustor from a 4600-pound-thrust turbojet engine to determine the amount of carbon deposition of AN-F-58 fuels and the effect of carbon formations in the combustor on the altitude operational limits. Three fuel blends conforming to AN-F-58 specification were prepared in order to determine the influence of boiling temperature and of aromatic content on carbon deposition. Results regarding carbon deposition and effect of carbon formations on altitude operational limits are provided.
Date:
June 24, 1949
Creator:
Wear, Jerrold D. & Douglass, Howard W.
System:
The UNT Digital Library
Wing-Tunnel Investigation at High Subsonic Speeds of the Lateral-Control Characteristics of an Aileron and a Stepped Spoiler on a Wing With Leading Edge Swept Back 51.3 Degrees
Report presenting a wind-tunnel investigation through a speed range from Mach number 0.30 to 0.90 to determine the lateral-control characteristics of a 20-percent-chord by 39-percent-semispan aileron and a 60-percent-semispan stepped spoilers on a semispan-wing model with aspect ratio of 3.06 with 51.3 degrees sweepback of the wing leading edge. The aileron rolling effectiveness decreased as the Mach number increased, while the spoiler rolling-moment effectiveness decreased with Mach number.
Date:
June 7, 1949
Creator:
Schneiter, Leslie E. & Hagerman, John R.
System:
The UNT Digital Library