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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Research Memorandums
 Collection: Technical Report Archive and Image Library
Tabulated Pressure Data for a Series of Controls on a 40 Deg Sweptback Wing at Mach Numbers of 1.61 and 2.01

Tabulated Pressure Data for a Series of Controls on a 40 Deg Sweptback Wing at Mach Numbers of 1.61 and 2.01

Date: November 8, 1957
Creator: Lord, D. R.
Description: An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers of 1.7 x l0(exp 6) and 3.6 x l0(exp 6) to determine the pressure distributions over a swept wing with a series of 14 control configurations. The wing had 40 deg of sweep of the quarter-chord line, an aspect ratio of 3.1, and a taper ratio of 0.4. Measurements were made at angles of attack from 0 deg to +/- 15 deg for control deflections from -60 deg to 60 deg. This report contains tabulated pressure data for the complete range of test conditions.
Contributing Partner: UNT Libraries Government Documents Department
Comparison of Several Methods of Cyclic De-Icing of a Gas-Heated Airfoil

Comparison of Several Methods of Cyclic De-Icing of a Gas-Heated Airfoil

Date: June 22, 1953
Creator: Gray, Vernon H. & Bowden, Dean T.
Description: Several methods of cyclic de-icing of a gas-heated airfoil were investigated to determine ice-removal characteristics and heating requirements. The cyclic de-icing system with a spanwise ice-free parting strip in the stagnation region and a constant-temperature gas-supply duct gave the quickest and most reliable ice removal. Heating requirements for the several methods of cyclic de-icing are compared, and the savings over continuous ice prevention are shown. Data are presented to show the relation of surface temperature, rate of surface heating, and heating time to the removal of ice.
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Compatibility of Metals with Liquid Fluorine at High Pressures and Flow Velocities

Compatibility of Metals with Liquid Fluorine at High Pressures and Flow Velocities

Date: January 1, 1958
Creator: Schmidt, H. W.
Description: No abstract available.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary wind-tunnel investigation of the effect of area suction on the laminar boundary layer over an NACA 64A010 airfoil

Preliminary wind-tunnel investigation of the effect of area suction on the laminar boundary layer over an NACA 64A010 airfoil

Date: April 26, 1948
Creator: Braslow, A. L.; Visconti, F. & Burrows, D. L.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Preliminary Wind-Tunnel Investigation of the Performance of Republic F-105 Wing-Root Inlet Configurations at Various Angles of Attack and a Mach Number of 2.01

Preliminary Wind-Tunnel Investigation of the Performance of Republic F-105 Wing-Root Inlet Configurations at Various Angles of Attack and a Mach Number of 2.01

Date: January 15, 1957
Creator: Kouyoumjian, W. L.
Description: A 1/13-scale model of the forebody of the Republic F-105 with twin-duct wing-root inlets was tested in the Langley 4- by 4-foot supersonic pressure tunnel through a range of angle of attack from -4 deg to 15 deg at a Mach number of 2.01 and a Reynolds number of approximately 3.4 x 10(exp 6) per foot. The tests were made with four configurations which incorporated varying amounts of sweep and stagger of the inlet leading edges, modifications to the areas of the boundary-layer diverter floor plate, and modifications to the area of the boundary-layer diverter bleed slots. The highest overall pressure recovery at an angle of attack of 0 deg (average total-pressure recovery, 0.84 mass-flow ratio, 0.98) was achieved with configuration having an inlet leading-edge sweep angle of 58 deg with no leading-edge stagger. Stagger was found to improve the angle-of- attack performance, but at a sacrifice in inlet efficiency for an angle of attack of 0 deg. The boundary-layer diverter floor height, of the order of one boundary-layer thickness, was satisfactory for bypassing the fuselage boundary layer. The boundary-layer diverter-plate bleed slots were effective in increasing the total-pressure recovery of the inlet. The total-pressure-recovery contour plots, taken at the ...
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Analysis of a Pneumatic Probe for Measuring Exhaust-Gas Temperatures with Some Preliminary Experimental Results

Analysis of a Pneumatic Probe for Measuring Exhaust-Gas Temperatures with Some Preliminary Experimental Results

Date: May 21, 1952
Creator: Scadron, Marvin D.
Description: A pneumatic probe based on continuity of mass flow through two restrictions separated by a cooling chamber was constructed to measure gas temperature at and beyond the limit of thermocouples. This probe consisted of a subsonic flat-plate orifice for the first restriction and a sonic-flow converging-diverging nozzle for the second restriction. The effect of variation in gas constants on the calibration is examined for common engine-exhaust gases. A high-temperature wind tunnel that allowed calibration of the probe at temperatures up to 2000 deg R and. Mach numbers up to 0.8 is described. Agreement to better than 30 deg R between pneumatic probe indication and the indication of a rake of radiation shielded thermocouples indicates that extrapolation of the calibration to higher temperatures is possible with fair accuracy.
Contributing Partner: UNT Libraries Government Documents Department
Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds

Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds

Date: September 18, 1951
Creator: Levine, Joseph & Kleinknecht, Kenneth S.
Description: A cascade impactor, an instrument for obtaining: the size distribution of droplets borne in a low-velocity air stream, was adapted for flight cloud droplet-size studies. The air containing the droplets was slowed down from flight speed by a diffuser to the inlet-air velocity of the impactor. The droplets that enter the impactor impinge on four slides coated with magnesium oxide. Each slide catches a different size range. The relation between the size of droplet impressions and the droplet size was evaluated so that the droplet-size distributions may be found from these slides. The magnesium oxide coating provides a permanent record. of the droplet impression that is not affected by droplet evaporation after the. droplets have impinged.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content

Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content

Date: July 11, 1951
Creator: Perkins, Porter J. & Kline, Dwight B.
Description: Flight icing-rate data obtained in a dense and. abnormally deep supercooled stratiform cloud system indicated the existence of liquid-water contents generally exceeding values in amount and extent previously reported over the midwestern sections of the United States. Additional information obtained during descent through a part of the cloud system indicated liquid-water contents that significantly exceeded theoretical values, especially near the middle of the cloud layer.. The growth of cloud droplets to sizes that resulted in sedimentation from the upper portions of the cloud is considered to be a possible cause of the high water contents near the center of the cloud layer. Flight measurements of the vertical temperature distribution in the cloud layer indicated a rate of change of temperature with altitude exceeding that of the moist adiabatic lapse rate. This excessive rate of change is considered to have contributed to the severity of the condition.
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Experimental investigation of effect of spike- tip and cowl-lip blunting on the internal performance of a two-cone cylindrical-cowl inlet at mach number 4.95

Experimental investigation of effect of spike- tip and cowl-lip blunting on the internal performance of a two-cone cylindrical-cowl inlet at mach number 4.95

Date: September 23, 1958
Creator: Weston, K. C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of air-cooled turbine blades in turbojet engine.  2:  Rotor blades with 15 fins in cooling-air passages

Experimental investigation of air-cooled turbine blades in turbojet engine. 2: Rotor blades with 15 fins in cooling-air passages

Date: August 1, 1950
Creator: Hickel, R. O. & Ellerbrock, H. H., Jr.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Investigation of Effects of Combustion-chamber Length and Inlet Total Temperature, Total Pressure, and Velocity on Afterburner Performance

Experimental Investigation of Effects of Combustion-chamber Length and Inlet Total Temperature, Total Pressure, and Velocity on Afterburner Performance

Date: June 3, 1957
Creator: King, C. R.
Description: Afterburner combustion efficiency - effects of chamber length, temperature, pressure and velocity.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of diffuser pressure ratio control with shock positioning limit on 28 inch ram-jet engine

Experimental investigation of diffuser pressure ratio control with shock positioning limit on 28 inch ram-jet engine

Date: January 15, 1957
Creator: Crowl, R. J.; Dunbar, W. R. & Wentworth, C. B.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental performance of a 5000-pound- thrust rocket chamber using a 20-percent- fluorine - 80-percent-oxygen mixture with RP-1

Experimental performance of a 5000-pound- thrust rocket chamber using a 20-percent- fluorine - 80-percent-oxygen mixture with RP-1

Date: April 24, 1957
Creator: Kutina, F. J., Jr.; Rothenberg, E. A. & Tomazic, W. A.
Description: Increased performance of rocket engine using fluorine-oxygen mixture with RP-1 fuel.
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of air-cooled turbine blades in turbojet engine.  1:  Rotor blades with 10 tubes in cooling-air passages

Experimental investigation of air-cooled turbine blades in turbojet engine. 1: Rotor blades with 10 tubes in cooling-air passages

Date: July 30, 1950
Creator: Ellerbrock, H. H., Jr. & Stepka, F. S.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental investigation of extreme internal flow turning at the cowl lip of an axisymetric inlet at a Mach number of 2.95

Experimental investigation of extreme internal flow turning at the cowl lip of an axisymetric inlet at a Mach number of 2.95

Date: May 13, 1958
Creator: Kowalski, K. L. & Weston, K. C.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Experimental Sea-level Static Investigation of a Short Afterburner

Experimental Sea-level Static Investigation of a Short Afterburner

Date: May 11, 1954
Creator: Harp, J. L., Jr.; Mallett, W. E. & Shillito, T. B.
Description: Sea-level static testing of turbojet engine afterburner.
Contributing Partner: UNT Libraries Government Documents Department
Exploratory Investigation of Performance of Experimental Fuelrich Hydrogen Combustion System

Exploratory Investigation of Performance of Experimental Fuelrich Hydrogen Combustion System

Date: June 25, 1958
Creator: Grobman, J. S. & Smith, A. L.
Description: Exploratory investigation of performance characteristics of fuel-rich hydrogen combustor.
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of a liquid hydrogen fuel system

Flight investigation of a liquid hydrogen fuel system

Date: August 19, 1957
Creator: Acker, L. W.; Christenson, H. H.; Gough, W. V. & Mulholland, D. R.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0

Performance of an Inlet Having a Variable-angle Two-dimensional Compression Surface and a Fixed-geometry Subsonic Diffuser for Application to Reduced Engine Rotative Speeds- Mach Numbers 0.66, 1.5, 1.7, and 2.0

Date: January 30, 1958
Creator: Allen, J. L.
Description: Air inlet for turbojet engines having variable angle two-dimensional compression surface and fixed-geometry subsonic diffuser.
Contributing Partner: UNT Libraries Government Documents Department
Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0

Performance of an All-internal Conical Compression Inlet With Annular Throat Bleed at Mach Number 5.0

Date: August 6, 1958
Creator: Obery, L. J. & Stitt, L. E.
Description: Internal compression inlet with throat bleed-off at hypersonic flow.
Contributing Partner: UNT Libraries Government Documents Department
Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50

Performance of an isentropic, all-internal- contraction, axisymmetric inlet designed for mach 2.50

Date: September 15, 1958
Creator: Anderson, B. H. & Bowditch, D. N.
Description: Performance of internal contraction, axisymmetric inlet with isentropic compression surfaces on cowl and centerbody at Mach 2.0 to 2.7.
Contributing Partner: UNT Libraries Government Documents Department
Performance of JP-4 fuel with fluorine- oxygen mixtures in 1000-pound-thrust rocket engines

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

Date: June 11, 1958
Creator: Douglass, H. W. & Nored, D. L.
Description: Fluorine-liquid oxygen mixture and injector design effects on JP-4 jet fuel performance in rocket engines.
Contributing Partner: UNT Libraries Government Documents Department
Performance of five short multielement turbojet combustors for hydrogen fuel in quarter-annulus duct

Performance of five short multielement turbojet combustors for hydrogen fuel in quarter-annulus duct

Date: July 22, 1958
Creator: Jones, R. E. & Rayle, W. D.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Performance of Isentropic Nose Inlets at Mach Number of 5.6

Performance of Isentropic Nose Inlets at Mach Number of 5.6

Date: May 6, 1954
Creator: Bernstein, H. & Haefeli, R. C.
Description: Isentropic nose inlet performance at mach 5.6.
Contributing Partner: UNT Libraries Government Documents Department