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Canard Hinge Moments and Longitudinal Stability of a 1/7-Scale Model of the Convair B-58 External Store in a Free-Flight Investigation at Mach Numbers From 0.94 to 2.58
Report presenting a longitudinal stability and control investigation of a model of the Convair B-58 external store over a range of Mach numbers. Normal force, chord force, and static and dynamic stability derivatives are provided. Abrupt pitching disturbances were created by step-function movements of the canard surface.
Date:
June 20, 1958
Creator:
Hollinger, James A.
System:
The UNT Digital Library
Altitude Starting Tests of a Small Solid Propellant Rocket
From Summary: "Four solid-propellant rocket engines of nominal 500-pound thrust were tested for starting characteristics at pressure altitudes ranging from 89,000 to 111,000 feet and at a temperature of -75^o F. Chamber pressures were measured on two of the runs. Average chamber pressures in these two runs were lower than expected, although action times agreed with the expected values."
Date:
June 21, 1957
Creator:
Sloop, John L. & Krawczonek, Eugene M.
System:
The UNT Digital Library
A Comparison of the Maneuvering Performance of a Monowing Versus a Cruciform Missile
Memorandum presenting an assessment of the importance of the addition lag of the monowing versus a cruciform shape on a missile.
Date:
June 1, 1955
Creator:
Matthews, Howard F. & Schmidt, Stanley F.
System:
The UNT Digital Library
Effect of pressure level on afterburner-wall temperatures
Report presenting an investigation conducted on a full-scale afterburner and turbojet engine to determine the effect of pressure level on afterburner-wall temperature. For a given ratio of cooling airflow to afterburner gas flow, the afterburner-wall temperature increased as afterburner-outlet pressure was increased. The results indicated that heat transfer by luminous radiation was not significant any pressure level investigated.
Date:
June 11, 1958
Creator:
Shillito, Thomas B. & Smolak, George R.
System:
The UNT Digital Library
Altitude Investigation of Can-Type Flame Holder in 20-Inchdiameter Ram-Jet Combustor
Memorandum presenting an investigation of a can-type flame holder employing a fuel-air-mixture control sleeve in a 20-inch-diameter ramjet combustor conducted by free-jet and direct-connect techniques at a simulated flight Mach number of 3.0 and altitudes from about 70,000 to 80,000 feet. Results regarding the effect of shortening combustion chamber and effect of pilot-burner variables are provided.
Date:
June 3, 1954
Creator:
Smolak, George R. & Wentworth, Carl B.
System:
The UNT Digital Library
Influence of Automatic Control of Roll Coupling and Pitch-Up on Tail Loads
Memorandum presenting a study of the effects of automatic augmentation or controlling systems on the tail loads experienced in rolling maneuvers and in pitch-up. The results were calculated on an analog computer and the equations of five degrees of freedom were used for the rolling maneuvers and three degrees of freedom for pitch-up.
Date:
June 17, 1957
Creator:
Stone, Ralph W., Jr.
System:
The UNT Digital Library
An Investigation of Jet Effects on Adjacent Surfaces
"The steady pressure loads as well as the temperature change on adjacent surfaces due to the presence of a propulsive jet at subsonic speeds is shown to be insignificant. Whereas at supersonic speeds the temperature effect might be expected to remain insignificant, the steady pressure loads were shown to increase greatly on surfaces downstream of the propulsive jet exit" (p. 1).
Date:
June 28, 1955
Creator:
Bressette, Walter E. & Faget, Maxime A.
System:
The UNT Digital Library
Empirical Cooling Correlation for an Experimental Afterburner With an Annular Cooling Passage
Memorandum presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation relates the average combustion-chamber wall temperature at a station near the combustion-chamber outlet to the temperatures of the cooling air and combustion gas, and to the mass flows of the cooling air and combustion gas.
Date:
June 26, 1952
Creator:
Koffel, William K. & Kaufman, Harold R.
System:
The UNT Digital Library
Attenuation of Tangential-Pressure Oscillations in a Liquid-Oxygen-n-Heptane Rocket Engine With Longitudinal Fins
Attenuation of tangent-pressure oscillation in liquid-oxygen-heptane rocket engine combustion chamber using longitudinal fin. Results regarding the engine performance with injector A, effect of fins with injector A, and destructiveness of screaming are provided.
Date:
June 28, 1956
Creator:
Priem, Richard J.
System:
The UNT Digital Library
Effect of Hinge-Line Position on the Oscillating Hinge Moments and Flutter Characteristics of a Flap-Type Control at Transonic Speeds
Free oscillation test to determine hinge moment of trailing-edge, flap control surface with various hinge-line positions at transonic speed. Results show that oscillating amplitude has a large effect on the control aerodynamic damping derivative and that the damping is unstable in the test Mach number range above about 0.90 for the hinge positions tested.
Date:
June 10, 1957
Creator:
Thompson, Robert F. & Moseley, William C., Jr.
System:
The UNT Digital Library
Investigation of Effect of Number and Width of Annular Flameholder Gutters on Afterburner Performance
Memorandum presenting an investigation of the effect of the number and width of annular flame-holder gutters on afterburner performance in a 26-inch-diameter afterburner test rig. The burner inlet temperature was held at 1250 degrees Fahrenheit. Results regarding the effect of gutter width on stability limits and effect of flame-holder blockage on pressure drop are provided.
Date:
June 3, 1954
Creator:
Henzel, James G., Jr. & Bryant, Lively
System:
The UNT Digital Library
Effects of Some Configuration Changes on Afterburner Combustion Performance
Report presenting an experimental investigation in a simulated afterburner test rig to determine the effects of some configuration variations on afterburner combustion performance. Results regarding the reduced-diameter flameholder, inclined radial-gutter flameholder, tapered-shell afterburner, and turbulence generators are provided.
Date:
June 12, 1957
Creator:
Nakanishi, Shigeo & King, Charles R.
System:
The UNT Digital Library
Experimental Investigation of Effects of Combustion-chamber Length and Inlet Total Temperature, Total Pressure, and Velocity on Afterburner Performance
Report presenting an investigation of the effects of afterburner-inlet total temperature, total pressure, velocity, fuel-air ratio, and afterburner combustion-chamber length on afterburner performance and stability limits using a cylindrical afterburner installed in a duct test rig. The afterburner was investigated over a range of total temperature, total pressure, velocity, and afterburner fuel-air ratios.
Date:
June 3, 1957
Creator:
King, Charles R.
System:
The UNT Digital Library
Aerodynamics of Oscillating Control Surfaces at Transonic Speeds
Memorandum presenting a discussion of oscillating flap-type and all-movable controls with particular emphasis on the aerodynamic forces and moments at transonic speeds. Hinge-moment results from recent wind-tunnel and rocket-powered-model tests are summarized for trailing-edge flap-type controls to illustrate the effects of control hinge-line position and profile shape on one-degree-of-freedom flutter of this type of control.
Date:
June 17, 1957
Creator:
Thompson, Robert F. & Clevenson, Sherman A.
System:
The UNT Digital Library
Factors Affecting Loads at Hypersonic Speeds
Report presenting a brief summary of current loads information at hypersonic speeds and some ways of estimating the loads on aircraft components when designing an aircraft.
Date:
June 19, 1957
Creator:
Henderson, Arthur, Jr. & Bertram, Mitchel H.
System:
The UNT Digital Library
Exploratory Investigation of Performance of Experimental Fuel-Rich Hydrogen Combustion System
Memorandum presenting an exploratory investigation conducted to determine the performance characteristics of a fuel-rich hydrogen combustor; in addition, the performance of an afterburner operating with the fuel-rich exhaust mixture was evaluated. Results regarding performance of the fuel-rich combustor, afterburner performance, and resonating combustion are provided.
Date:
June 25, 1958
Creator:
Smith, Arthur L. & Grobman, Jack S.
System:
The UNT Digital Library
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