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Some effects of wing fences on the lateral stability derivatives of a 60 degree delta wing oscillating continuously in yaw

Description: Report presenting an investigation at low speed to determine some of the effects of wing fences on the lateral stability derivatives of a flat-plate 60 degree delta-wing model oscillating continuously in yaw. Results regarding the variation with angle of attack, effect of frequency, effect of amplitude, number of fences, and some effects of fence geometric characteristics are provided.
Date: July 11, 1956
Creator: Riley, Donald R.
Partner: UNT Libraries Government Documents Department

Transonic flight tests to determine zero-lift drag and pressure recovery of nacelles located at the wing tips on a 45 degree sweptback wing and body combination

Description: Report presenting the zero-lift drag of a sweptback wing and body combination with nacelles with NACA 1-50-250 nose inlets locate in the wing tips as determined by flight tests of rocket-powered models at transonic speeds. Results regarding the pressure recovery and the effect of the nacelles on it are also provided.
Date: January 11, 1952
Creator: Hoffman, Sherwood & Pepper, William B., Jr.
Partner: UNT Libraries Government Documents Department

Analytical and experimental studies of a divided-flow ram-jet combustor

Description: From Introduction: "The investigation reported herein is a continuation of a ram-jet-combustor design program being conducted at the NACA Lewis laboratory. The purpose of this broad program is to establish basic design criteria for combustors operating over wide range of fuel-air ratio with low pressure losses and high combustion efficiency, and to utilize these design criteria in the development of practical ram-jet combustors."
Date: January 11, 1954
Creator: Dangle, E. E.; Friedman, Robert & Cervenka, Adolph J.
Partner: UNT Libraries Government Documents Department

A transonic investigation by the free-fall method of an airplane configuration having 45 degrees sweptback wing and tail surfaces

Description: Report presenting a free-fall investigation of airplanes in the transonic range using a configuration with 45 degree sweptback wing and tail surfaces. The lift, drag, and longitudinal static and dynamic stability and control characteristics were obtained at a range of operating lift coefficients and Mach numbers.
Date: June 11, 1953
Creator: Faber, Stanley & Eggleston, John M.
Partner: UNT Libraries Government Documents Department

Utilization of external-compression diffusion principle in design of shock-in-rotor supersonic compressor blading

Description: Report presenting the application of the external-compression principle to a cascade of blades in an attempt to achieve a closer approach to isentropic contraction ratios in supersonic compressor blading. Tests of a rotor designed to incorporate the external-compression principle are provided. Results regarding overall performance, performance at design speed and peak efficiency, off-design performance, and some considerations for future designs are provided.
Date: September 11, 1953
Creator: Creagh, John W. R. & Klapproth, John F.
Partner: UNT Libraries Government Documents Department

The effects at transonic speeds of thickening the trailing edge of a wing with a 4-percent-thick circular-arc airfoil

Description: Report presenting an investigation of the effects of a systematic variation of trailing-edge thickness of a symmetrical, circular-arc airfoil on the aerodynamic force, moment, base-pressure, and wake fluctuations using the transonic-bump testing technique. Results regarding the effects of a systematic variation of the trailing-edge thickness, investigation of a boattailed trailing edge, and wake fluctuation characteristics are provided.
Date: December 11, 1951
Creator: Cleary, Joseph W. & Stevens, George L.
Partner: UNT Libraries Government Documents Department

Experimental investigation of the zero-lift drag of a fin-stabilized body of fineness ratio 10 at Mach numbers between 0.6 and 10

Description: Report presenting free-flight measurements of the zero-lift drag of a cruciform-finned body at a range of Mach and Reynolds numbers. Results regarding experimental total drag, comparison of theory with experiment, comparison of experiment with NOL results, boundary-layer transition, Reynolds number effects, and fin leading-edge shape are provided.
Date: June 11, 1953
Creator: James, Carlton S. & Carros, Robert J.
Partner: UNT Libraries Government Documents Department

Low-speed pressure-distribution investigation of a spoiler and a spoiler-slot-deflector on a 30 degree sweptback wing-fuselage model having an aspect ratio of 3, a taper ratio of 0.5, and NACA 65A004 airfoil section

Description: Report presenting an investigation on a 30 degree sweptback wing-fuselage model in the 300 mph 7- by 10-foot tunnel to determine the effect of flap-type spoilers and spoiler-slot-deflectors on the chordwise and spanwise pressure distributions over the wing and controls. The results regarding the tabulated pressure, section force, and moment coefficients for six spanwise stations and curves of the variation of the total integrated force and moment coefficients with angle of attack for various control projections are provided.
Date: January 11, 1956
Creator: Hammond, Alexander D.
Partner: UNT Libraries Government Documents Department

Flight-determined static lateral stability and control characteristics of a swept-wing fighter airplane to a Mach number of 1.39

Description: Report presenting an investigation of the static lateral stability characteristics of a swept-wing fighter-type airplane with three vertical-tail configurations and two wing configurations at an altitude of 40,000 feet over a range of Mach numbers. Data was obtained in several conditions, including constant-heading sideslips and wings-level turns, aileron rolls, and abrupt rudder pulses. Results regarding the sideslip characteristics, lateral control, and control effectiveness derivatives are provided.
Date: March 11, 1957
Creator: Matranga, Gene J. & Peele, James R.
Partner: UNT Libraries Government Documents Department

Wind-tunnel investigation of stall control by suction through a porous leading edge on a 37 degree sweptback wing of aspect ratio 6 at Reynolds numbers from 2.50 x 10(exp 6) to 8.10 x 10(exp 6)

Description: Report presenting an investigation of the effects of suction through a porous leading-edge surface in the 19-foot pressure tunnel on a wing with 37 degrees of sweepback of the leading edge, an aspect ratio of 6, taper ratio of 0.5, and NACA 64(sub 1)-212 airfoil sections normal to the 27-percent-chord line. Results regarding the wing without flaps, wing with trailing-edge flaps, and power requirements for porous-leading-edge suction are provided.
Date: March 11, 1953
Creator: Graham, Robert R. & Jacques, William A.
Partner: UNT Libraries Government Documents Department

Static longitudinal stability and control characteristics of a model of a 45 degree swept-wing fighter airplane at Mach numbers of 1.41, 1.61, and 2.01

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the static longitudinal stability and control characteristics of a model of a 45 degree swept-wing fighter airplane at three Mach numbers. The results indicate that the static margin, which was fairly constant through the lift range, decrease from 32 to 27 percent mean aerodynamic chord with increase in Mach number from 1.41 to 2.01.
Date: July 11, 1956
Creator: Driver, Cornelius & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department

Experimental sea-level static investigation of a short afterburner

Description: Report presenting a sea-level static investigation to determine the performance and some design principles for a short afterburner. The power section of a 12-stage axial-flow turbojet engine was used and the afterburner was designed to fit within the length required for the tail pipe used on the standard nonafterburning model.
Date: May 11, 1954
Creator: Harp, James L.; Shillito, Thomas B. & Mallett, William E.
Partner: UNT Libraries Government Documents Department

The static longitudinal characteristics of a twisted and cambered 45 degree sweptback wing at Mach numbers up to 0.96

Description: Report presenting a 45 degree sweptback wing of aspect ratio 3, with twist and a distributed type of camber, tested in combination with a body of fineness ratio 12.5 to determine the lift, drag, and pitching-moment characteristics.
Date: August 11, 1958
Creator: Sammonds, Robert I. & Reynolds, Robert M.
Partner: UNT Libraries Government Documents Department

Some experiments relating to the problem of simulation of hot jet engines in studies of jet effects on adjacent surfaces at a free-stream Mach number of 1.80

Description: Report presenting an investigation at a free-stream Mach number of 1.80 in a blowdown tunnel to study the effect on the pressure distribution of a zero-angle-of-attack wing surface when certain exhaust parameters of a hot turbojet engine are varied. Results regarding shock wave and pressure coefficients are provided.
Date: July 11, 1956
Creator: Bressette, Walter E.
Partner: UNT Libraries Government Documents Department

Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Description: From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on the problem."
Date: August 11, 1958
Creator: Stoney, William E., Jr.
Partner: UNT Libraries Government Documents Department

Performance of JP-4 fuel with fluorine-oxygen mixtures in 1000-pound-thrust rocket engines

Description: Report presenting seven injectors of four different types tested for use with JP-4-oxygen-fluorine propellant combinations. High characteristics velocities were obtained over the complete range of 0- to 70-percent fluorine in the oxidant. Results regarding the injector performance, heat rejection, injector with triplet-jet elements in skewed array, and fluorine addition are provided.
Date: June 11, 1958
Creator: Nored, Donald L. & Douglass, Howard W.
Partner: UNT Libraries Government Documents Department

Investigation of spoiler-slot-deflector ailerons and other spoiler ailerons on a 45 degree sweptback-wing--fuselage combination at Mach numbers from 0.60 to 1.03

Description: Report presenting an investigation in the transonic tunnel to determine the characteristics of several flap-type spoiler ailerons, lower-surface deflector ailerons, and spoiler-slot-deflector ailerons. Six-component force and moment data were obtained at a range of Mach numbers and angles of attack.
Date: September 11, 1956
Creator: West, F. E., Jr.; Whitcomb, Charles F. & Schmeer, James W.
Partner: UNT Libraries Government Documents Department

The aerodynamic characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing through a Mach number range from 0 to 2.4 obtained from various sources

Description: "A summary and analysis have been made of the results of various investigations to determine the aerodynamic characteristics of a supersonic aircraft configuration. The configuration has a wing with 40 degree sweepback at the quarter-chord line, aspect ratio 4, taper ratio 0.5, and 10-percent-thick circular-arc sections normal to the quarter-chord line. Experimental data were available for a Mach number range from 0.16 to 2.32. Results obtained from wing-flow, rocket-model, transonic-bump, and tunnel tests are presented and, where possible, are supplemented by empirical and theoretical calculations" (p. 1).
Date: April 11, 1952
Creator: Spearman, M. Leroy & Robinson, Ross B.
Partner: UNT Libraries Government Documents Department

Preliminary Results From Free Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular-Piloted Baffle-Type Flameholder

Description: Report presenting an investigation in a free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths, three lengths of the shroud which separated the bypass air from the burning stream, and four fuel-distribution systems were investigated over a range of fuel-air ratios and a range of engine air flows. Results regarding the engine performance and ignition data, effect of fuel profile on combustion efficiency, total-pressure ratio, and distribution of static pressure in the main air stream are provided.
Date: May 11, 1955
Creator: Rayle, Warren D.; Smith, Ivan D. & Wentworth, Carl B.
Partner: UNT Libraries Government Documents Department

Preliminary Results From Free-Jet Tests of a 48-Inch-Diameter Ram-Jet Combustor With an Annular Can-Type Flame Holder

Description: Report presenting an investigation in an NACA free-jet facility of a ramjet engine with an experimental 48-inch-diameter combustor. Three combustor lengths and three fuel-distribution systems were investigated over a range of fuel-air ratios and at two air flows. Results regarding the combustor performance and ignition data, velocity profile, and starting characteristics are provided.
Date: May 11, 1955
Creator: Wentworth, Carl B.; Dobson, Wilbur F. & Rayle, Warren D.
Partner: UNT Libraries Government Documents Department

Theoretical Maximum Performance of Liquid Fluorine - Liquid Oxygen Mixtures With JP-4 Fuel as Rocket Propellants

Description: Memorandum presenting a calculation of theoretical values of rocket performance parameters for JP-4 fuel and various mixtures of liquid fluorine and liquid oxygen, assuming equilibrium and frozen composition during the expansion process. Data were calculated at several equivalence ratios for each assigned fluorine-oxygen mixture. Some of the parameters explored include specific impulse, combustion-chamber temperature, nozzle-exit temperature, equilibrium composition, mean molecular weight, characteristic velocity, coefficient of thrust, and ratio of nozzle-exit area to throat area.
Date: October 11, 1954
Creator: Gordon, Sanford & Wilkins, Roger L.
Partner: UNT Libraries Government Documents Department

Lift and Drag of the Bell X-5 Research Airplane in the 45 Degree Sweptback Configuration at Transonic Speeds

Description: Memorandum presenting a flight investigation of the Bell X-5 variable-sweep research airplane in the 45 degree wing sweptback configuration over a range of Mach numbers. Lift and drag values are presented and a comparison is made with data obtained with a wing sweepback of 59 degrees.
Date: July 11, 1956
Creator: Nugent, Jack
Partner: UNT Libraries Government Documents Department

Design and Test of Mixed-Flow Impellers 4: Experimental Results for Impeller Models MF-1 and MF-2 With Changes in Blade Height

Description: From Summary: "Modifications A and B of impeller model MFI-1 and A, B, and C of impeller model MFI-2 were investigated experimentally in an attempt to determine what allowance in blade height should be made for boundary layer and viscous losses in an impeller designed for isentropic compressible flow. A gradual increase in blade height was arbitrarily made from inlet to outlet in anticipation of a gradual build-up of boundary layer. Apparently there was a rapid build-up of boundary layer near the inlet in the experimental case rather than a gradual one. Therefore, the proper allowance for boundary layer cannot be described from the data obtained."
Date: February 11, 1954
Creator: Hamrick, Joseph T.; Beede, William L. & Withee, Joseph R., Jr.
Partner: UNT Libraries Government Documents Department