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Effects of Combinations of Aspect Ratio and Sweepback at High Subsonic Mach Numbers
Report discussing an investigation to determine the effects of sweepback and low aspect ratio on the aerodynamic characteristics of a wing at high subsonic Mach numbers. Tests were performed at aspect ratios of 2, 3, and 5 and sweepback angles of 0, 30, and 45 degrees. Generally, sweepback and low aspect ratio were found to both delay and lessen the effects of compressibility.
Date:
June 4, 1947
Creator:
Adler, Alfred A.
System:
The UNT Digital Library
Preliminary Investigation of Effects of Gamma Radiation on Age-Hardening Rate of an Aluminum-Copper Alloy
"A preliminary investigation was made to determine the effects of gamma radiation on the age-hardening rate of an aluminum-copper alloy at temperatures of 32 and 70 degrees Fahrenheit. The gamma radiation from a 100-milligram radium source appeared to have no significant effect on the age-hardening rate of the alloy. A metallographic examination of the test specimens showed no microstructural changes that could be attributed to gamma radiation" (p. 1).
Date:
June 20, 1947
Creator:
Kittel, J. Howard
System:
The UNT Digital Library
An Investigation of the Low-Speed Stability and Control Characteristics of Swept-Forward and Swept-Back Wing in the Ames 40- by 80-Foot Wind Tunnel
"An investigation has been made at large scale of the characteristics of highly swept wings. Data were obtained at several angles of sideslip on wings having angles of sweep of plus or minus 45 degrees, plus or minus 30 degrees, and 0 degrees. The airfoil sections of the wings varied from approximately NACA 0015 at the root to NACA 23009 at the tip. Each wing was investigated with flaps under flection, partial-span split flaps deflected 60 degrees, full-span split flaps defected 60 degrees and split-flap-type ailerons deflected plus or minus 15 degrees" (p. 1).
Date:
June 10, 1947
Creator:
McCormack, Gerald M. & Stevens, Victor I., Jr.
System:
The UNT Digital Library
Results of flight tests at supersonic speeds to determine the effect of body nose fineness ratio on body and wing drag
Report presenting flight tests of rocket-powered models at supersonic speeds to determine the effect of nose fineness ratio of winged bodies on total and component drag at high Mach numbers. Wingless models of three nose fineness ratios and winged models of two nose fineness ratios flown through a range of Mach numbers. Results regarding total drag, body drag, and wing drag are provided.
Date:
June 26, 1947
Creator:
Katz, Ellis R.
System:
The UNT Digital Library
An Investigation of the Lateral-Control Characteristics of Spoilers on a High-Aspect-Ratio Wing of NACA 65-210 Section in the Langley 8-Foot High Speed Tunnel
Report presenting a lateral-control investigation of 3- and 6-percent chord spoilers projecting on the upper surface of a wing of high-aspect ratio. The spoilers were found to give large rolling moments at Mach numbers below the Mach number corresponding to the break in the rolling-moment-coefficient curves. Results regarding section pressure distributions, rolling-moment characteristics, normal-force characteristics, pitching-moment characteristics, wing-torsional considerations, and hinge-moment characteristics are provided.
Date:
June 24, 1947
Creator:
Luoma, Arvo A.
System:
The UNT Digital Library
A fuel-distribution control for continuous-flow manifold injection on reciprocating engines
"A fuel-distribution control for continuous-flow manifold injection on reciprocating engines is described. A method is installation of the control on an engine is suggested. The device controlled the flow to four spring-loaded nozzles within 2 percent of perfect distribution over a wide range of fuel-flow rates and the distribution was practically unaffected by uneven discharge-nozzle pressures" (p. 1).
Date:
June 6, 1947
Creator:
Gold, Harold & Straight, David M.
System:
The UNT Digital Library
Some pressure-distribution measurements on a swept-wing at transonic speeds by the NACA wing-flow method
Report presenting results of chordwise pressure-distribution measurements on a 45 degree sweptback wing at transonic speeds. The two stations for measuring were located at the 18 percent chord from the root and the 87 percent chord. The changes in pressure distribution with Mach number did not indicate any appreciable net loss in section lift, but did indicate large increases in the section drag and diving moment.
Date:
June 6, 1947
Creator:
Johnston, J. Ford & Danforth, Edward C. B.
System:
The UNT Digital Library
Performance of a 20-inch steady-flow ram jet at high altitudes and ram-pressure ratios
Report presenting the results of an investigation conducted in the altitude wind tunnel to determine the performance of a 20-inch ramjet. The investigation was conducted at a range of altitudes and ram-pressure ratios using preheated 62-octane fuel. A net thrust of 8135 pounds educed to standard sea-level conditions, a net-thrust coefficient of 0.74, and an overall efficiency of 12.6 percent were attained at Mach number 1.845 at which the engine with a 5-foot combustion chamber was operated.
Date:
June 25, 1947
Creator:
Perchonok, Eugene; Sterbentz, William H. & Wilcox, Fred A.
System:
The UNT Digital Library
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
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