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Preliminary Free-Flight Study of the Drag and Stability of a Series of Short-Span Missiles at Mach Numbers From 0.9 to 1.3

Description: Memorandum presenting a preliminary free-flight study of the drag and stability of a series of short-span missile configurations with 80, 85, and 90 degrees of fin leading-edge sweep. Increasing the fin sweep decreased the drag markedly.
Date: February 8, 1956
Creator: Hall, James Rudyard
Partner: UNT Libraries Government Documents Department

A Transonic Wind-Tunnel Investigation of the Effects of Body Indentation, as Specified by the Transonic Drag-Rise Rule, on the Aerodynamic Characteristics and Flow Phenomena of a 45 Degree Sweptback-Wing-Body Combination

Description: Memorandum presenting a comparison of the aerodynamic characteristics and flow phenomena at transonic speeds for a 45 degree sweptback wing mounted alternatively on a cylindrical body and an indented body. Indentation eliminated the zero-lift drag rise associated with the wing at a Mach number of 1. Results regarding the lift, drag, and pitching moment, flow surveys, level-flight characteristics, and flow phenomena are provided.
Date: February 9, 1953
Creator: Robinson, Harold L.
Partner: UNT Libraries Government Documents Department

Investigation of Ejection Release Characteristics of Bluff TX-28 and Turnabout TX-28 Stores From a 1/17-Scale Simulated Bomb Bay of the Republic F-105 Airplane at Mach Numbers of 1.39 and 1.98 : Coord. No. AF-222

Description: Memorandum presenting a study of two bluff modifications of the TX-28 store in the 27- by 27-inch preflight jet of the Langley Pilotless Aircraft Research Station. Successful releases were made with both stores at near-sea-level conditions with high ejection velocities. Results regarding the Bluff TX-28 and Turnabout TX-28 are provided.
Date: February 5, 1957
Creator: Lee, John B.
Partner: UNT Libraries Government Documents Department

Flight Experience With Two High-Speed Airplanes Having Violent Lateral-Longitudinal Coupling in Aileron Rolls

Description: "During flight tests of two high-speed airplane configurations, violent cross-coupled lateral and longitudinal motions were encountered following abrupt rudder-fixed aileron rolls. The speeds involved ranged from a Mach number of 0.7 to 1.05. The motions were characterized by extreme variations in angles of attack and sideslip which resulted in load factors as large as 6.7g (negative) and 7g (positive) normal acceleration and 2g transverse acceleration" (p. 1).
Date: February 4, 1955
Partner: UNT Libraries Government Documents Department

Investigation of Aerodynamic Characteristics in Pitch and Sideslip of a 45 Degree Sweptback-Wing Airplane Model With Various Vertical Locations of Wing and Horizontal Tail: Static Longitudinal Stability and Control, M = 2.01

Description: Memorandum presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of various vertical locations of the wing and horizontal tail on the aerodynamic characteristics in pitch and of a supersonic airplane configuration at Mach number 2.01. The model was equipped with a wing and horizontal tail, each having a 45 degree sweep and an aspect ratio of 4. The configurations investigated included a high-wing, a mid-wing, and a low-wing arrangement, each with four different horizontal tail locations varying from a position 0.208 semispan below to 0.556 semispan above the body center line.
Date: February 21, 1956
Creator: Spearman, M. Leroy & Driver, Cornelius
Partner: UNT Libraries Government Documents Department

Some Results of Flight Testing of Ski-Equipped Aircraft at the Naval Air Test Center

Description: Memorandum presenting the results of flight testing of four different ski-equipped airplanes. Two types of skis were tested: hydro-skis designed to operate under or on the water surface and general-purpose skis designed to operate on a variety of surfaces but not underwater. A breakdown of the ski performance for each plane and ski combination is provided.
Date: February 4, 1955
Creator: Beck, Preston E.
Partner: UNT Libraries Government Documents Department

Pressure Recovery, Drag, and Subcritical Stability Characteristics of Three Conical Supersonic Diffusers at Stream Mach Numbers From 1.7 to 2.0

Description: A study of a 20 degree and a 25 degree half-angle high mass-flow ratio conical supersonic inlet was made on a 16-inch ram jet in the 8- by 6-foot supersonic tunnel. A greater range of stable subcritical operation was obtained with the low mass-flow ratio inlets; a greater range was obtained with the 25 degree than with the 20 degree half-angle low mass-flow ratio inlet. The high mass-flow ratio inlet had the least drag.
Date: February 27, 1952
Creator: Nussdorfer, Theodore J.; Obery, Leonard J. & Englert, Gerald W.
Partner: UNT Libraries Government Documents Department

Some Operating Experience and Problems Encountered During Operation of a Free-Jet Facility

Description: During a free-jet investigation of a 28-inch ram-jet engine at a Mach number of 2.35, flow pulsation at the engine inlet were discovered which proved to have an effect on the engine performance and operational characteristics, particularly the engine rich blowout limits. This report discusses the finding of the flow pulsations, their elimination, and effect. Other facility characteristics, such as the establishment of flow simulation and the degree of subcritical operation of the diffuser, are also explained.
Date: February 13, 1957
Creator: McAulay, John E. & Prince, William R.
Partner: UNT Libraries Government Documents Department

Explosion and Combustion Properties of Alkylsilanes 1: Temperature-Composition Limits of Explosion for Methyl-,Dimethyl-,Trimethyl-,Tetramethyl-,and Vinylsilane at Atmospheric Pressure

Description: "The explosion limits of five alkylsilanes were determined as a function of temperature and composition at a pressure of 1 atmosphere. Over a fuel concentration range of 2 to 10 percent, the lowest temperatures (zero C) below which explosion did not occur for the five fuels studied were: tetramethylsilane (CHsub3)sub4Si, 450 degrees; trimethlysilane (CHsub3)sub3SiH, 310 degrees;dimethylsilane (CHsub3)sub2SiHsub2, 220 degrees; methylsilane CHsub3SiHsub3, 130 degrees; and vinylsilane Hsub2C=CH-SiHsub3, 90 degrees. Explosion limits for hydrocarbons analogous to these silanes fall in a temperature range of 500 degrees to 600 degrees C" (p. 1).
Date: February 5, 1954
Creator: Schalla, Rose L. & McDonald, Glen E.
Partner: UNT Libraries Government Documents Department

Effect of Water on Carbon Monoxide-Oxygen Flame Velocity

Description: "The flame velocities were measured of 20 percent oxygen and 80 percent carbon monoxide mixtures containing either light water or heavy water. The flame velocity increased from 34.5 centimeters per second with no added water to about 104 centimeters per second for a 1.8 percent addition of light water and to 84 centimeters per second for an equal addition of heavy water. The addition of heavy water caused greater increases in flame velocity with equilibrium hydrogen-atom concentration than would be predicted by the Tanford and Pease square-root relation" (p. 1).
Date: February 5, 1954
Creator: McDonald, Glen E.
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

Preliminary Investigation of a Variable-Area Auxiliary Air-Intake System at Mach Numbers From 0 to 1.3

Description: "A variable-area auxiliary air scoop in combination with a fixed-area nose intake was tested at Mach numbers from 0 to 1.3. The purpose of the investigation was to evaluate the effectiveness of such an auxiliary intake in improving the net thrust of an intake-engine combination over a range of speeds. The results indicated that the internal flow was always stable and that improvements in net thrust would be realized at Mach numbers up to about 1.1 for an intake design Mach number of 1.3" (p. 1).
Date: February 25, 1953
Creator: Scherrer, Richard; Stroud, John F. & Swift, John T.
Partner: UNT Libraries Government Documents Department

Experimental Investigation of the Effect of Forebody Bluntness on the Pressure Recovery and Drag of a Twin-Scoop Inlet-Body Combination at Mach Numbers of 1.4 and 1.7

Description: Memorandum presenting the pressure recovery, mass flow, and drag of a twin-scoop inlet-body combination measured at Mach numbers 1.4 and 1.7 at zero angle of attack. Tests were made of the inlet-body combination with an ogival forebody, an ogival forebody with a small amount of bluntness near the tip, and two forebodies of elliptical longitudinal section. Results regarding the effect of forebody bluntness on pressure recovery, effect of forebody bluntness on mass-flow ratio, and the effects of forebody bluntness on drag are provided.
Date: February 14, 1952
Creator: Stroud, John F.
Partner: UNT Libraries Government Documents Department

Tests in the Ames 40- by 80-Foot Wind Tunnel of an Airplane Model With an Aspect Ratio 4 Triangular Wing and an All-Movable Horizontal Tail - High-Lift Devices and Lateral Controls

Description: Memorandum presenting tests of a triangular-wing-airplane model equipped with high-lift devices and lateral and directional controls. The model consisted of an aspect ratio 4 triangular wing in combination with a fuselage of fineness ratio 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail. Results regarding the effects of flap deflection and tail incidence on the pitching moment characteristics, lift and drag characteristics, and rudder effects are provided.
Date: February 20, 1953
Creator: Franks, Ralph W.
Partner: UNT Libraries Government Documents Department

Tests in the Ames 40- by 80-Foot Wind Tunnel of Two Airplane Models Having Aspect Ratio 2 Trapezoidal Wings of Taper Ratios 0.33 and 0.20

Description: Memorandum presenting tests of two airplane models with trapezoidal wings of aspect ratio 2 and taper ratios of 0.33 and 0.20. For each model, a fuselage with a fineness ratio of 12.5, a thin, triangular, vertical tail with a constant-chord rudder, and a thin, unswept, all-movable horizontal tail was used. Tests of the wing-fuselage vertical-tail configuration and of the complete airplane model were made for both models.
Date: February 16, 1953
Creator: Franks, Ralph W.
Partner: UNT Libraries Government Documents Department

Comparison of Performance of Two Aerodynamically Similar 14-Inch-Diameter Single-Stage Compressor Rotors of Different Chord Length

Description: Memorandum presenting a comparison of the performance of two aerodynamically similar single-stage rotors of different chord length. Results regarding short-chord-rotor performance, long-chord-rotor performance, comparison of overall performance, blade-element performance, rotating stall, and separation-parameter analysis are provided.
Date: February 10, 1958
Creator: Kussoy, Marvin I. & Bachkin, Daniel
Partner: UNT Libraries Government Documents Department

Study of Some Dielectric Properties of Suspensions of Magnesium Particles in Mineral Oil

Description: The variation of dielectric constant has been measured as a function of the concentration of magnesium particles; the shape, size, and degree of oxidation of the particles; the temperature; and the frequency of oscillation. The variation of dielectric constant and settling rate was investigated as a function of time. Also investigated were the effects of particle concentration, shape and time on dielectric losses.
Date: February 19, 1954
Creator: Altshuller, Aubrey P.
Partner: UNT Libraries Government Documents Department

Summary Report on Analytical Evaluation of Air and Fuel Specific-Impulse Characteristics of Several Nonhydrocarbon Jet-Engine Fuels

Description: Memorandum presenting an analytical evaluation of the air and fuel specific-impulse characteristics of magnesium, magnesium-octene-1 slurries, aluminum, aluminum-octene-1 slurries, boron, boron-octene-1 slurries, carbon, hydrogen, methylnaphthalene, diborane, and pentaborane. Adiabatic constant-pressure combustion temperature, air specific impulse, fuel specific impulse, and equilibrium composition data are given for each fuel over a range of equivalence ratios.
Date: February 19, 1953
Creator: Breitwieser, Roland; Gordon, Sanford & Gammon, Benson
Partner: UNT Libraries Government Documents Department

Experimental Investigation of a Method of Wave-Drag Reduction for Combinations Employing Quasicylindrical Bodies and Swept Wings at Supersonic Speeds

Description: "Axisymmetric and nonaxisymmetric body distortions designed by the method of NACA TN 3722 were tested to determine the amount of wave-drag reduction obtainable when applied to swept-wing-body combinations over a Mach number range of 1.39 to 1.97. Two wings of aspect ratios 1.33 and 2.67 were tested on different bodies. Both the axisymmetric and nonaxisymmetric distortions produced drag reductions" (p. 1).
Date: February 19, 1957
Creator: Hickey, Daniel P.
Partner: UNT Libraries Government Documents Department

Correlation Between Hydrogen Pressure and Protective Action of Additives in the Molten Sodium Hydroxide - Nickel System

Description: Memorandum presenting an investigation of the effect of various metallic additives on the molten sodium hydroxide - nickel system. The hydrogen evolved from such systems was measured and the evolution was correlated with the effect of the metal on mass transfer. Results regarding a check with standard tests, purging, presence of two valences for chromium, reaction time of the additive, and pressure within nickel crucibles are provided.
Date: February 9, 1956
Creator: May, Charles E.
Partner: UNT Libraries Government Documents Department

Dynamic Response of Turbine-Blade Temperature to Exhaust-Gas Temperature for Gas-Turbine Engines

Description: "The frequency of blade temperature to exhaust gas temperature is presented for two locations in the blade and at several operating conditions. The frequency response was determined by Fourier analysis of transient data. Two analytical methods are presented, and results are compared with experimental data. Dynamic response of turbine-blade temperature to exhaust-gas temperature exhibited the form of an approximate first-order lag" (p. 1).
Date: February 20, 1952
Creator: Hood, Richard & Phillips, William E., Jr.
Partner: UNT Libraries Government Documents Department

Performance of Supersonic Scoop Inlets

Description: A brief summary is made of the performance of a series of variable-geometry type scoop inlets investigated at the Lewis Laboratory on a model of the X-3 airplane fuselage. Data are presented for a range of inlet mass-flow ratios over a Mach number range from 0 to 2 and from 0 degrees to 12 degrees angle of attack. Rounded-lip inlets are found to give satisfactory performance to a Mach number of 1.5. Use of sharp rather than blunt lip configurations is shown to provide considerable gains in available thrust at Mach number 2.0 but penalize take-off performance to the extent that auxiliary air intakes may be required.
Date: February 18, 1952
Creator: Weinstein, M. I.
Partner: UNT Libraries Government Documents Department

Investigation of Pressure Losses in Several Turbosupercharger Nozzle Hoses

Description: Memorandum presenting surveys of the impact pressure of the flow to obtain information for determining pressure losses in four different turbosupercharger nozzle boxes. The data indicated substantial differences in total head loss among the boxes and the existence of sharply defined high-loss regions in portions of the nozzle annulus.
Date: February 11, 1947
Creator: Lord, Albert M. & Donnola, Joseph
Partner: UNT Libraries Government Documents Department

Transonic Free-Flight Investigation of the Longitudinal Aerodynamic Characteristics of a 1/10-Scale Steel-Wing of the Northrop MX-775A Missile With Leading-Edge Extensions, Inboard Trailing-Edge Flaps, and a Speed Brake on the Vertical Tail

Description: Memorandum presenting results of a free-flight investigation over a range of Mach and Reynolds numbers to determine the longitudinal aerodynamic characteristics of the Northrop MX-775A missile. The missile has a wing, body, and vertical tail, but has no horizontal tail. Results regarding basic data, drag, trim, lift and static stability, damping, and static pressure are provided.
Date: February 11, 1955
Creator: Arbic, Richard G.
Partner: UNT Libraries Government Documents Department