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The effect of cowling on cylinder temperatures and performance of a Wright J-5 engine

Description: This report presents the results of tests conducted to determine the effect of different amounts and kinds of cowling on the performance and cylinder temperatures of a standard Wright J-5 engine. These tests were conducted in conjunction with drag and propeller tests in which the same cowlings were used. Four different cowlings were investigated varying from the one extreme of no cowling on the engine to the other extreme of the engine completely cowled and the cooling air flowing inside the co… more
Date: May 2, 1929
Creator: Schey, Oscar W. & Biermann, Arnold E.
Partner: UNT Libraries Government Documents Department
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High Altitude Performance Investigation of J65-B-3 Turbojet Engine With Both JP-4 and Gaseous Hydrogen Fuels

Description: Memorandum presenting an investigation to determine the performance of the J65-B-3 turbojet engine with JP-4 and gaseous-hydrogen fuels. With JP-4 fuel, the maximum altitude for stable combustion was from about 60,000 to 65,000 feet, and the ultimate blowout limit was at an altitude of about 75,000 feet. The steady-state performance with either fuel decreased considerably with increasing altitude.
Date: April 2, 1957
Creator: Kaufman, Harold R.
Partner: UNT Libraries Government Documents Department
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Collection and summary of flap-type-aileron rolling-effectiveness data at zero lift as determined by rocket-powered model tests at Mach numbers between 0.6 and 1.6

Description: Report presenting a collection and summary of the wing-aileron rolling-effectiveness data obtained as part of an investigation of lateral control using rocket-powered test vehicles in free flight over a range of Mach numbers. Some effects of trailing-edge angle, aileron-chord ratio, aileron span and location, aspect ratio, wing sweepback, and wing-tail interference are provided.
Date: September 2, 1955
Creator: Strass, H. Kurt; Stephens, Emily W.; Fields, E. M. & Schult, Eugene D.
Partner: UNT Libraries Government Documents Department
open access

Analysis of effects of airplane characteristics and autopilot parameters on a roll-command system with aileron rate and deflection limiting

Description: From Summary: "The dynamic characteristics of an airplane with a proportional-gain roll-control autopilot are discussed. A comparison of three different high-speed fighter airplanes is presented. The dynamic effects of time lags and various gains in the system are described."
Date: September 2, 1955
Creator: Schy, Albert A. & Gates, Ordway B., Jr.
Partner: UNT Libraries Government Documents Department
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Theoretical investigation of the effects of configuration changes on the center of pressure shift of a body-wing-tail combination due to angle of attack and Mach number at transonic and supersonic speeds

Description: Report presenting a theoretical investigation to study the effects of systematic changes in configuration of a representative airframe on the center-of-pressure travel due to changes in angle of attack and in Mach number. The airframe was an unbanked canard missile configuration with low-aspect-ratio coplanar wing and tail surfaces of triangular plan form. Results regarding the center-of-pressure shift due to angle of attack, center-of-pressure shift due to Mach number, and combined effects of … more
Date: September 2, 1955
Creator: Spahr, J. Richard
Partner: UNT Libraries Government Documents Department
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Engine performance of alloy 73J turbine blades cast to predetermined grain sizes

Description: Report presenting an investigation to determine the suitability of alloy 73J as a turbojet turbine-blade alloy and the effect of grain size on engine operating life. Blades made of alloy 73J were run in a full-scale J33-9 turbojet engine under cyclic conditions. Results regarding the macroexamination of blades, engine life, engine life against stress-rupture life, blade failures, blade elongation, metallographic results, and blade dimensions and the possible effects of overdimensions are provid… more
Date: July 2, 1954
Creator: Johnston, James R.; Gyorgak, Charles A. & Weeton, John W.
Partner: UNT Libraries Government Documents Department
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An investigation at high subsonic speeds of the pressure distributions on a 45 degree sweptback vertical tail in sideslip with and without a 45 degree sweptback horizontal tail located on the fuselage center line

Description: Report presenting an investigation in the high-speed tunnel at high subsonic speeds and several angles of attack of the chordwise pressure distribution at six spanwise stations on a 45 degree sweptback, untapered vertical tail in sideslip. The presence of the horizontal tail slightly increased the value of section normal-force coefficients on the vertical tail but did not materially alter the nature of the load distribution.
Date: November 2, 1954
Creator: Wiley, Harleth G. & Moseley, William C., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87

Description: Memorandum presenting results of a supersonic flutter investigation of three low-aspect-ratio control surfaces. Two controls were all-movable but the third had a fixed cutout. Results regarding the experiments and calculations are provided.
Date: May 2, 1958
Creator: Morgan, Homer G.; Figge, Irving E. & Presnell, John G., Jr.
Partner: UNT Libraries Government Documents Department
open access

Effects of Modifications to a Control Surface on a 6-Percent-Thick Unswept Wing on the Transonic Control-Surface Flutter Derivatives

Description: Transonic flutter derivatives for unswept wing control surface configurations determined by pressure cell measurements. The control surfaces were mounted on a wing with an aspect ratio of 3, a taper ratio of 0.6, and a wing-thickness ratio of 0.06. Results regarding aerodynamic balance, vortex generators, splitter-plate configurations, and wedges are provided.
Date: May 2, 1958
Creator: Wyss, John A.; Sorenson, Robert M. & Gambucci, Bruno J.
Partner: UNT Libraries Government Documents Department
open access

Preliminary flight survey of aerodynamic noise on an airplane wing

Description: Report presenting a brief series of airplane-wing aerodynamic-noise and boundary-layer-profile measurements made in flight as part of an extended investigation of boundary-layer noise. Results regarding the boundary layer data and ratio of root-mean-square sound pressure to the dynamic pressure are provided.
Date: March 2, 1956
Creator: Mull, Harold R. & Algranti, Joseph S.
Partner: UNT Libraries Government Documents Department
open access

NACA Investigations of Icing-Protection Systems for Turbojet-Engine Installations

Description: "Investigations have been made in flight and in wind tunnels to determine which components of turbojet installations are most critical in icing conditions, and to evaluate several methods of icing protection. From these studies, the requirements necessary for adequate icing protection and the consequent penalties on engine performance can be estimated. Because investigations have indicated that the compressor-inlet screen constitutes the greatest icing hazard and is difficult to protect, comple… more
Date: May 2, 1951
Creator: von Glahn, Uwe; Callaghan, Edmund E. & Gray, Vernon H.
Partner: UNT Libraries Government Documents Department
open access

General Theory of Aerodynamic Instability and the Mechanism of Flutter

Description: "The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom were determined. The problem resolves itself into the solution of certain definite integrals, which were identified as Bessel functions of the first and second kind, and of zero and first order. The theory, based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing section theory relating to the steady case" (p. 291).
Date: May 2, 1934
Creator: Theodorsen, Theodore
Partner: UNT Libraries Government Documents Department
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Large-Scale Wind-Tunnel Tests of an Airplane Model With a 45 Degree Sweptback Wing of Aspect Ratio 2.8 With Area Suction Applied to Trailing-Edge Flaps and With Several Wing Leading-Edge Modifications

Description: Memorandum presenting an investigation of an airplane model to determine the effect of area suction trailing-edge flaps and several leading-edge modifications on the aerodynamic characteristics of a 45 degree sweptback wing. The wing had an aspect ratio of 2.8 and a taper ratio of 0.17.
Date: November 2, 1956
Creator: Koenig, David G. & Aoyagi, Kiyoshi
Partner: UNT Libraries Government Documents Department
open access

Tests With Hydrogen Fuel in a Simulated Afterburner

Description: Report presenting an investigation in a 16-inch-diameter simulated afterburner using gaseous hydrogen fuel. Results regarding combustion efficiency, afterburner pressure losses, spontaneous ignition, and a heat-balance check are provided.
Date: July 2, 1956
Creator: Kerslake, W. R. & Dangle, E. E.
Partner: UNT Libraries Government Documents Department
open access

Organophosphorus Compounds in Rocket-Engine Applications

Description: Report discussing the ignition-delay determinations of three organophosphorous fuels with nitric acid oxidants at simulated altitude conditions with a small-scale rocket engine.
Date: April 2, 1954
Creator: Ladanyi, Dezso J. & Hennings, Glen
Partner: UNT Libraries Government Documents Department
open access

Some Research on the Lift and Stability of Wing-Body Combinations

Description: The present paper summarizes and correlates broadly some of the research results applicable to fin-stabilized ammunition. The discussion and correlation are intended to be comprehensive, rather than detailed, in order to show general trends over the Mach number range up to 7.0. Some discussion of wings, bodies, and wing-body interference is presented, and a list of 179 papers containing further information is included. The present paper is intended to serve more as a bibliography and source of … more
Date: July 2, 1959
Creator: Purser, Paul E. & Fields, E. M.
Partner: UNT Libraries Government Documents Department
open access

Performance of a Short Turbojet Combustor With Hydrogen Fuel in a Quarter-Annulus Duct and Comparison With Performance in a Full-Scale Engine

Description: Memorandum presenting an investigation of a number of short turbojet combustor configurations for hydrogen fuel in a quarter-annulus duct. The best combustor liner consisted of an annular primary zone and a secondary zone composed of T-shaped channels sloping from the primary zone to the combustor wall.
Date: July 2, 1956
Creator: Friedman, Robert; Norgren, Carl T. & Jones, Robert E.
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of Low-aspect-ratio Wings at High Supersonic Mach Numbers

Description: Memorandum presenting some recently obtained data on the aerodynamic characteristics of low-aspect-ratio wings at supersonic Mach number of 4.04 and 6.9 and discusses some new methods of predicting the lift and drag of such wings. The plan forms, airfoil sections, and thickness ratios of the wings tested are provided.
Date: November 2, 1953
Creator: Ulmann, Edward F. & Bertram, Mitchel H.
Partner: UNT Libraries Government Documents Department
open access

Characteristics of a 15-Percent-Chord and a 35-Percent-Chord Plain Flap on the NACA 0006 Airfoil Section at High Subsonic Speeds

Description: Memorandum presenting wind-tunnel tests to determine the aerodynamic characteristics of a 15-percent- and a 35-percent-chord plain trailing-edge flap on the NACA 0006 airfoil section. Simultaneous measurements of section lift, drag, and pitching moment were made over a range of Mach numbers, angles of attack, and flap deflections.
Date: October 2, 1947
Creator: Ilk, Richard J.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Analysis of Problem of Determining Experimental Performance of Air-Cooled Turbine 3: Methods for Determining Power and Efficiency

Description: Suggested formula are given for determining air-cooled turbine-performance characteristics, such as power and efficiency, as functions of certain parameters. These functions, generally being unknown, are determined from experimental data obtained from specific investigations. Special plotting methods for isolating the effect of each parameter are outlined.
Date: August 2, 1950
Creator: Ellerbrock, Herman H., Jr. & Ziemer, Robert R.
Partner: UNT Libraries Government Documents Department
open access

Lateral-control investigation of flap-type controls on a wing with quarter-chord line swept back 60 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section: transonic bump method

Description: Report presenting an investigation by the transonic-bump method through a range of Mach numbers in the high-speed 7- by 10-foot tunnel to determine the lateral-control characteristics of 30-percent-chord flap-type controls of various spans and locations. The wing of the semispan fuselage-wing combination had 60 degrees of sweepback of the quarter-chord line, a taper ratio of 0.6, an aspect ratio of 4.0, and an NACA 65A006 airfoil section parallel to the free air stream.
Date: March 2, 1950
Creator: Vogler, Raymond D.
Partner: UNT Libraries Government Documents Department
open access

Preliminary analysis of effects of air cooling turbine blades on turbojet-engine performance

Description: The effects of turbine-blade cooling on engine performance were analytically investigated for a turbojet engine in which cooling air is bled from the engine compressor. The analysis was made for a constant turbine-inlet temperature and a range of altitudes to determine the minimum cooling requirements to permit substitution of nonstrategic materials in turbine blading. The results indicate that, for a constant inlet temperature, air cooling of the turbine blades increases the specific fuel cons… more
Date: August 2, 1950
Creator: Schramm, Wilson B.; Nachtigall, Alfred J. & Arne, Vernon L.
Partner: UNT Libraries Government Documents Department
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