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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.
Contributing Partner: UNT Libraries Government Documents Department
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 ...
Contributing Partner: UNT Libraries Government Documents Department
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.
Contributing Partner: UNT Libraries Government Documents Department
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