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Method for Estimating Lift Interference of Wing-Body Combinations at Supersonic Speeds

Description: Memorandum presenting the use of the modified slender-body method to predict the lift and moment interference of triangular wing-body combinations adapted to combinations with other than triangular wings. The methods are applied to the prediction of the lit-curve slopes of nearly 100 triangular, rectangular, and trapezoidal wing-body configurations.
Date: December 31, 1951
Creator: Nielsen, Jack N. & Kaattari, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of turbines suitable for use in a turbojet engine with high compressor ratio and low compressor-tip speed 5: experimental performance of two-stage turbine with downstream stator

Description: An experimental investigation of a highly loaded two-stage turbine with a downstream stator revealed that (1) at equivalent design work and speed the brake internal efficiency was 0.81 and the maximum efficiency obtained was 0.85, and (2) the downstream stator left very little energy in the form of tangential velocity in the gas and, in general, performed well with 0.78 recovery being obtained at equivalent design work and speed.
Date: October 21, 1951
Creator: Davison, Elmer H.; Petrash, Donald A. & Schum, Harold J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of altitude ignition, acceleration and steady-state operation with single combustor of J47 turbojet engine

Description: Report describing an investigation conducted with a single combustor from a J47 turbojet engine using weathered aviation gasoline and several spark-plug modifications to determine altitude ignition, acceleration, and steady-state operating characteristics. Results regarding ignition, acceleration, altitude operational limits, combustion efficiency, and pressure loss are provided.
Date: March 5, 1951
Creator: Cook, William P. & Butze, Helmut F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effectiveness of Thermal-Pneumatic Airfoil-Ice-Protection System

Description: From Summary: "Icing and drag investigations were conducted in the NACA Lewis icing research tunnel employing a combination thermal-pneumatic de-icer mounted on a 42-inch-chord NACA 0018 airfoil. The de-icer consisted of a 3-inch-wide electrically heated strip symmetrically located about the leading edge with inflatable tubes on the upper and lower airfoil surfaces aft of the heated area. The entire de-icer extended to approximately 25 percent of chord. A maximum power density of 9.25 watts per… more
Date: April 13, 1951
Creator: Gowan, William H., Jr. & Mulholland, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculated Performance of a Direct-Air Nuclear Turbojet-Powered Airplane Using a Split-Flow Reactor and a Separated-Type Shield

Description: Memorandum presenting an analysis made to estimate the performance of a direct-air nuclear turbojet-powered airplane using a split-flow reactor and a separated-type shield. The analysis was for flight Mach numbers of 0.9 and 1.5 and covered a range of altitudes, reactor-wall temperatures, turbine-inlet temperatures, compressor pressure ratios, and airplane lift-drag ratios.
Date: February 1951
Creator: Doyle, R. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight Instrument for Measurement of Liquid-Water Content in Clouds at Temperatures Above and Below Freezing

Description: "A principle formerly used in an instrument for cloud detection was further investigated to provide a simple and rapid means for measuring the liquid-water content of clouds at temperatures above and below freezing. The instrument consists of a small cylindrical element so operated at high surface temperatures that the impingement of cloud droplets creates a significant drop in the surface temperature. The instrument is sensitive to a wide range of liquid-water content and was calibrated at one… more
Date: March 6, 1951
Creator: Perkins, Porter J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Simplified Instrument for Recording and Indicating Frequency and Intensity of Icing Conditions Encountered in Flight

Description: Memorandum presenting an instrument for recording and indicating the frequency and intensity of aircraft icing conditions to obtain statistical icing data over worldwide air routes during routine airline operations. Data of this type is needed to provide pertinent meteorological information necessary for the optimum design of ice-protection systems. The features that make this particular instrument desirable include the simplicity of operation, freedom from maintenance and operating problems, a… more
Date: July 3, 1951
Creator: Perkins, Porter J.; McCullough, Stuart & Lewis, Ralph D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Adaptation of a Cascade Impactor to Flight Measurement of Droplet Size in Clouds

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" (p. 1).
Date: September 18, 1951
Creator: Levine, Joseph & Kleinknecht, Kenneth S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Meteorological Data Obtained During Flight in a Supercooled Stratiform Cloud of High Liquid-Water Content

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 dr… more
Date: July 11, 1951
Creator: Perkins, Porter J. & Kline, Dwight B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine. 7: Rotor-Blade Fabrication Procedures

Description: "An experimental investigation was conducted to determine the cooling effectiveness of a wide variety of air-cooled turbine-blade configurations. The blades, which were tested in the turbine of a - commercial turbojet engine that was modified for this investigation by replacing two of the original blades with air-cooled blades located diametrically opposite each other, are untwisted, have no aerodynamic taper, and have essentially the same external profile. The cooling-passage configuration is … more
Date: September 12, 1951
Creator: Long, Roger A. & Esgar, Jack B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Spark Ignition of Flowing Gases. 2: Effect of Electrode Parameters on Energy Required to Ignite a Propane-Air Mixture

Description: From Summary: "Research was conducted to determine the effect of the electrode parameters of spacing, configuration, and material' on the energy required for ignition of a flowing propane-air mixture. In addition, the data were used to indicate the energy distribution along the spark length and to confirm previous observations concerning the effect of spark duration on ignition energy requirements. The data were obtained with a mixture at a fuel-air ratio of 0.0835 (by weight), a pressure of 3 … more
Date: December 18, 1951
Creator: Swett, Clyde C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of the Descent Characteristics of Bodies of Revolution Simulating Anti-Personnel Bombs

Description: "An investigation has been conducted in the Langley 20-foot free spinning tunnel to study the relative behavior in descent of a number of homogeneous balsa bodies of revolution simulating anti-personnel bombs with a small cylindrical exploding device suspended approximately 10 feet below the bomb. The bodies of revolution included hemispherical, near-hemispherical, and near-paraboloid shapes. The ordinates of one near-paraboloid shape were specified by the Office of the Chief of Ordnance, U. S.… more
Date: December 19, 1951
Creator: Scher, Stanley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XF3H-1 Airplane

Description: Report presenting an investigation of the low-speed, power-off stability and control characteristics of a model of the McDonnell XF3H-1 airplane. Flight testing occurred in the clean and slat- and flaps-extended conditions over a range of lift coefficients.
Date: October 11, 1951
Creator: Draper, John W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral-Control Characteristics and Dihedral Effect of a Wing-Body Combination With a Variable-Incidence Triangular Wing and Wing-Tip Ailerons at a Mach Number of 1.52

Description: Memorandum presenting an investigation of aileron effectiveness and dihedral effect for a wing-body combination with a variable-incidence triangular wing with modified half-delta controls at the wing tips. The tests were conducted at a Mach number of 1.52 at a Reynolds number of 0.82 million. The experimental value of aileron effectiveness at 0 degrees angle of attack was approximately 78 percent of the value predicted by linear theory, and the effectiveness decreased with increasing wing angle… more
Date: January 10, 1951
Creator: Scherrer, Richard & Dennis, David H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Calculated Performance of a Mercury-Compressor-Jet Powered Airplane Using a Nuclear Reactor as an Energy Source

Description: Memorandum presenting an analysis of a system consisting of a mercury turbine-driven air compressor a mercury condenser wherein heat was added to the compressed air. The heat addition to the mercury is accomplished in an intermediate heat exchanger (mercury boiler) which has a liquid metal, other than mercury, circulating through the opposite side and through a nuclear reactor. Results regarding the turbine-exhaust pressure, turbine-inlet pressure, condenser-inlet Mach number, effect of nacelle… more
Date: September 26, 1951
Creator: Doyle, R. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Measurement of distortion in second experimental control rod for argonne naval reactor with constant transverse temperature gradient and uniform longitudinal temperature distribution

Description: Report presenting measurements of the thermal distortion of a stainless-steel clad, cadmium-silver reactor control rod. The temperature pattern of the rod is described. The maximum reduction in clearance obtained in the tests was 0.203 inch.
Date: September 26, 1951
Creator: Nagey, T. F. & Lietzke, A. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of the Liquid-Metal Turbojet Cycle for Propulsion of Nuclear Powered Aircraft

Description: From Introduction: "The present report gives an analysis of the design point performance of nuclear powered liquid-metal turbojet engines. The effect of varying the assumptions necessary to calculate gross weight and reactor heat release from engine data is presented."
Date: November 19, 1951
Creator: Wachtl, W. W. & Rom, F. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of the Liquid-metal Turbojet Cycle for Propulsion of Nuclear Powered Aircraft

Description: Report presenting an analysis of the nuclear powered liquid-metal turbojet cycle for a wide range of engine operating conditions at a range of flight Mach numbers and altitudes. The method of analysis and working charts are presented to facilitate investigations beyond the scope of this report.
Date: November 19, 1951
Creator: Rom, F. E. & Wachtl, W. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Apparatus for obtaining a supersonic flow of very short duration and some drag measurements obtained with its use

Description: From Introduction: "The auxiliary apparatus described in this paper was constructed to meet this need and has been developed to a point where satisfactory measurements of relative drag can be obtained. In this paper, the apparatus is described and some comparisons are made between the results obtained with this apparatus and the measurements of free-fall, rocket, and supersonic-tunnel techniques."
Date: July 23, 1951
Creator: Yeates, John E., Jr.; Bailey, F. J., Jr. & Voglewede, T. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Jet Tests of a 6.5-Inch-Diameter Ram-Jet Engine at Mach Numbers 1.81 and 2.00

Description: Report presenting testing of a 6.5-inch-diameter ramjet engine with a design Mach number of 2.13 and a short-flame-length combustor. Performance characteristics are provided for a range of Mach numbers and fuel-air ratios. Results regarding thrust, drag tests, static pressure, and combustion efficiencies are provided.
Date: March 7, 1951
Creator: Faget, Maxime A.; Watson, Raymond S. & Bartlett, Walter A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some properties of beryllium oxide and beryllium oxide - columbium ceramals

Description: High-temperature tensile and thermal-shock investigations were conducted on beryllium oxide and beryllium oxide plus columbium metal additions. X-ray diffraction and metallographic results are given. The tensile strength of 6150 pounds per square inch for beryllium oxide at 1800 degrees F compared favorably with the zirconia bodies previously tested. Additions of 2, 5, 8, 10, 12, and 15 percent by weight of columbium metal failed to improve the shock resistance over that of pure beryllium oxide. more
Date: March 2, 1951
Creator: Robards, C. F. & Gangler, J. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation of the control-surface flutter derivatives of an NACA 65(sub 1)-213 airfoil in the Ames 16-foot high-speed wind tunnel

Description: Report presenting a determination of control-surface flutter derivatives for a sinusoidally oscillating control surface mounted on a two-dimensional fixed airfoil for a range of reduced frequency. Results regarding subsonic results and transonic results are provided.
Date: December 21, 1951
Creator: Wyss, John A. & Sorenson, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of air-cooled turbine blades in turbojet engine 9: evaluation of the durability of noncritical rotor blades in engine operation

Description: The durability of five different structural or cooling configurations or combination of both of air-cooled blades made of noncritical materials was investigated in a modified turbojet engine. The greater part of the investigation was conducted at an engine speed of 11,500 rpm, a turbine-inlet temperature of approximately 1670 degrees F, and a cooling-air to combustion gas flow ratio per blade of 0.05. The results of the investigation indicated that air-cooled blades made of noncritical metals c… more
Date: December 5, 1951
Creator: Stepka, Francis S. & Hickel, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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