UNT Libraries Government Documents Department - 42 Matching Results

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open access

Altitude investigation of 16 flame-holder and fuel-system configurations in tail-pipe burner

Description: From Introduction: "The data obtained for each configuration are presented in a manner to show the effects of fuel distribution and flame-holder design on net thrust, specific fuel consumption, exhaust-gas temperature, combustion efficiency, operable range of tail-pipe-burner fuel-air ratios, and maximum altitude limit."
Date: December 12, 1951
Creator: Grey, Ralph E.; Krull, H. G. & Sargent, A. F.
open access

Altitude Wind Tunnel Investigation of the Performance of Compressor, Combustor, and Turbine Components of Prototype J47D (RX1-1) Turbojet Engine

Description: "As a portion of an over-all performance investigation of the prototype J47D (RX-1) turbojet engine, performance of the compressor, combustor, and turbine components has been determined in the Lewis altitude wind tunnel over a range of altitude from 5000 to 55,000 feet and at flight Mach numbers from 0.19 to 0.92. Investigations were conducted with the engine operating on an electronic control schedule and slow with a two-lever control system by which fuel flow and exhaust-nozzle area could be … more
Date: December 21, 1951
Creator: Farley, John M.
open access

Arrangement of Bodies of Revolution in Supersonic Flow to Reduce Wave Drag

Description: "The wave drag of a combination of slender bodies of revolution at zero angle of attack is studied with a view to determining the arrangements for which the total drag is a minimum. Linearized theory is used to calculate the pressure distribution in the field surrounding the bodies. The interference drag coefficient is computed for different arrangements. The special cases of two bodies and of a three-body combination with bilateral symmetry are considered" (p. 1).
Date: December 17, 1951
Creator: Friedman, Morris D.
open access

Arrangement of Bodies of Revolution in Supersonic Flow to Reduce Wave Drag

Description: "The wave drag of a combination of slender bodies of revolution at zero angle of attack is studied with a view to determining the arrangements for which the total drag is a minimum. Linearized theory is used to calculate the pressure distribution in the field surrounding the bodies. The interference drag coefficient is computed for different arrangements" (p. 1).
Date: December 17, 1951
Creator: Friedman, Morris D.
open access

Comparison of drag, pressure recovery, and surface pressure of a scoop-type inlet and an NACA submerged inlet at transonic speeds

Description: Report presenting an investigation of a solid half body modified to mount a scoop inlet and a submerged inlet while maintaining the same entrance geometry, afterbody, and diffuser for both inlets. Comparative pressure-recovery, pressure-distribution, and drag data were obtained for the two inlet types.
Date: December 17, 1951
Creator: Frank, Joseph L. & Taylor, Robert A.
open access

Comparison of Semispan and Full-Span Tests of a 47.5 Degrees Sweptback Wing With Symmetrical Circular-Arc Sections and Having Drooped-Nose Flaps, Trailing-Edge Flaps, and Ailerons

Description: Report presenting an investigation to compare the characteristics of a full-span and a semispan highly swept wing in order to evaluate the general validity of the semispan wing testing technique. Results regarding the lift, drag, and pitching-moment characteristics are provided.
Date: December 5, 1951
Creator: Lipson, Stanley & Barnett, U. Reed, Jr.
open access

Effect of Formation Position on Load Factors Obtained on F2H Airplanes

Description: Report presenting results of a four-plane formation flight with twelve pull-up maneuvers in the form of plots of maximum load factor attained versus airplane position for three combinations of four F2H airplanes. The load factor was generally found to increase toward the end of the formation, and movements of the lead plane that are too sharp might cause excessive loads on the last plane in the formation.
Date: December 7, 1951
Creator: Huss, Carl R. & Hamer, Harold A.
open access

Effect of Section Thickness and Trailing-Edge Radius on the Performance of NACA 65-Series Compressor Blades in Cascade at Low Speeds

Description: Report presenting tests of NACA 65-series compressor blades cambered to an isolated airfoil lift coefficient of 1.2 at several maximum section thicknesses to obtain the effect of maximum section thickness on section operating characteristics. Information about surface pressure trends, design angle-of-attack selection, drag, operating range, and critical Mach number is also provided. Changing the section thickness was not found to significantly affect the design angle of attack selected.
Date: December 13, 1951
Creator: Herrig, L. Joseph; Emery, James C. & Erwin, John R.
open access

Effect of spark repetition rate on the ignition limits of a single tubular combustor

Description: The effect of spark repitition rate on the altitude ignition limits of a single tubular (turbojet engine) combustor was investigated. An increase in sparking rate from 3 to 140 sparks per second reduced the ignition limiting combustor-inlet pressure about 2 to 4 inches of mercury for air-flow rates of 1.87 and 2.80 pounds per second per square foot.520::At 3.75 pounds pe At 3.75 pounds per second per square foot, the corresponding reduction was 4 to 12 inches of mercury. The trend was similar f… more
Date: December 6, 1951
Creator: Foster, Hampton H.
open access

The effects at transonic speeds of thickening the trailing edge of a wing with a 4-percent-thick circular-arc airfoil

Description: Report presenting an investigation of the effects of a systematic variation of trailing-edge thickness of a symmetrical, circular-arc airfoil on the aerodynamic force, moment, base-pressure, and wake fluctuations using the transonic-bump testing technique. Results regarding the effects of a systematic variation of the trailing-edge thickness, investigation of a boattailed trailing edge, and wake fluctuation characteristics are provided.
Date: December 11, 1951
Creator: Cleary, Joseph W. & Stevens, George L.
open access

Effects of altitude on turbojet engine performance

Description: From Summary: "Component and over-all performance characteristics of several turbojet engines investigated in the altitude facilities of the NACA Lewis Laboratory during the last several years are summarized to indicate the effects of altitude on turbojet engine performance. Data presented show that failure of turbojet engine performance to generalize for all altitudes can be traced to reductions in compressor efficiency, corrected air flow, and combustion efficiency at altitude. In addition, i… more
Date: December 21, 1951
Creator: Fleming, William A.
open access

Effects of horizontal-tail position, area, and aspect ratio on low-speed static longitudinal stability and control characteristics of a 60 degrees triangular-wing model having various triangular-all-movable horizontal tails

Description: Report presenting a low-speed investigation in the stability tunnel to determine the static longitudinal stability and control characteristics of a 60 degree triangular-wing model with various triangular-all-movable horizontal tails. An all-movable trail of 10 percent of the wing area and aspect ratio 2.31 was investigated in 17 tail positions, including positions above, below, and to the rear of the assumed center of gravity.
Date: December 14, 1951
Creator: Jaquet, Byron M.
open access

Effects on control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degrees sweptback wing at a Mach number of 1.9

Description: Report presenting the effect of control effectiveness of systematically varying the size and location of trailing-edge flaps on a 45 degree sweptback wing at a Mach number of 1.9. The wing model had an aspect ratio of 2.5, a taper ratio of 0.625, and 6-percent-thick hexagonal airfoil sections. Results regarding the rolling-moment and yawing-moment coefficients, lift, rolling-moment, and pitching-moment effectiveness parameters, and flap characteristics are provided.
Date: December 4, 1951
Creator: Jacobsen, Carl R.
open access

Elevated Temperature Properties of Titanium Carbide Base Ceramals Containing Nickel or Iron

Description: Elevated-temperature properties of titanium carbide base ceramals containing nickel or iron were determined in oxidation, modulus of rupture, tensile strength, and thermal-shock resistance. These materials followed the general growth law and exhibited two stages in oxidation. The following tensile strengths were found at 2000 degrees F: 13.3 weight percent nickel, 16, 150 pounds per square inch; 11.8 weight percent iron, 12,500 pounds per square inch; unalloyed titanium carbide, 16,450 pounds p… more
Date: December 3, 1951
Creator: Cooper, A. L. & Colteryahn, L. E.
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.
open access

Experimental Investigation of an 0.8 Hub-Tip Radius-Ratio, Nontwisted-Rotor-Blade Turbine

Description: "An experimental investigation of a 0.8 hub-tip radius ratio, nontwisted-rotor-blade turbine designed for a stagnation-pressure ratio of 2.5 and an equivalent mean blade speed of 643 feet per second was made in a cold-air turbine with (a) nontwisted stator blades, and (b) twisted stator blades designed to maintain zero rotor-inlet incidence angles. Turbine efficiencies of the order of 0.85 at the design point were obtained with a nontwisted-rotor-blade turbine with a hub-tip radius ratio of 0.8… more
Date: December 12, 1951
Creator: Silvern, David H. & Slivka, William R.
open access

Experimental Investigation of Effect of Jet Exit Configuration on Thrust and Drag

Description: Memorandum presenting an investigation of the problem of performance losses occurring when airplanes equipped with afterburner and cooling-air ejector installations are flown with the afterburner inoperative. Two sources of the performance losses occurring under some operation conditions were identified: an overexpansion of the propulsive jet and an internal shock system and the excessive pumping action resulting from the off-design.
Date: December 20, 1951
Creator: Callaghan, Edmund E. & Coles, Willard D.
open access

Exploratory investigation at high and low subsonic Mach numbers of two experimental 6-percent-thick airfoil sections designed to have high maximum lift coefficients

Description: Report presenting an investigation to determine if thin airfoils with increased values of low-speed maximum lift coefficient but also retain the basic advantages of thin sections at high Mach numbers can be developed. Several experimental thin airfoil sections were developed from an analysis of airfoil data and two of them were investigated at high and low subsonic Mach numbers. Results regarding the low-speed characteristics and high-speed characteristics are provided.
Date: December 14, 1951
Creator: Loftin, Laurence K., Jr. & von Doenhoff, Albert E.
open access

Flow Separation Ahead of a Blunt Axially Symmetric Body at Mach Numbers 1.76 to 2.10

Description: "The pressure distribution and drag were determined for a spherical-nosed axially symmetric body with thin projecting rods at Mach numbers of 1.76, 1.93, and 2.10. The upstream projection distance of the rods was varied over a wide range to study changes in the character of the flow separation and to determine the variation of drag and pressure distribution with tip projection. Drag coefficients between 0.18 and 0.30 were obtained for most tip projections at each Mach number" (p. 1).
Date: December 12, 1951
Creator: Moeckel, W. E.
open access

Free-Flight Investigation to Determine Force and Hinge-Moment Characteristics at Zero Angle of Attack of a 60 Degrees Sweptback Half-Delta Tip Control on a 60 Degrees Sweptback Delta Wing at Mach Numbers Between 0.68 and 1.44

Description: Report presenting a free-flight investigation of two rocket-powered control research models to determine the force and hinge-moment characteristics at zero angle of attack of a half-delta tip control on a delta wing. Results regarding the control hinge moments, control normal force, and calculated hinge moments are provided.
Date: December 3, 1951
Creator: Martz, C. William; Church, James D. & Goslee, John W.
open access

Free-Spinning Tunnel Investigation of a 1/20-Scale Model of the Douglas X-3 Airplane

Description: Report discussing the spin and spin-recovery characteristics of a model of the Douglas X-3 airplane in a free-spinning tunnel. The pitching-moment characteristics of the scale model were not found to be typical of larger scale results. The results indicated that at an altitude range of 15,000 to 30,000 feet, the X-3 will not exhibit unusual trim tendencies and it will be difficult to obtain erect spins unless the ailerons are full with the spin.
Date: December 26, 1951
Creator: Hultz, Burton E.
open access

Full-scale investigation of cooling shroud and ejector nozzle for a turbojet engine: afterburner installation

Description: From Summary: "A full-scale ejector cooling investigation was made on a turbojet engine - afterburner installation in the NACA Lewis altitude wind tunnel. Ejector performance was studied at primary exhaust-gas temperatures from 2700 degrees to 3400 degrees R (corresponding to ejector temperature ratios from 2.0 to 5.0), primary pressure ratios from 1.79 to 3.4, secondary air flows up to 29 percent of the primary gas flow, and for diameter ratios from 1.08 to 1.42 and spacing ratios from 0.04 to… more
Date: December 17, 1951
Creator: Wallner, Lewis E. & Jansen, Emmert T.
open access

Fundamental Flame Velocities of Pure Hydrocarbons 3: Extension of Tube Method of High Flame Velocities - Acetylene-Air Mixtures

Description: Memorandum presenting an extension of the tube method of measuring flame velocities to fundamental flame velocities of 141 centimeters per second. The extension was accomplished by reducing the flame-tube diameter from 25 to 12.5 millimeters. Results regarding the gas flow and spatial flame velocity, flame surface area, and fundamental flame velocity are provided.
Date: December 3, 1951
Creator: Levine, Oscar & Gerstein, Melvin
open access

Generalization of Turbojet and Turbine-Propeller Engine Performance in Windmilling Condition

Description: Windmilling characteristics of several turbojet and turbine-propeller engines were investigated individually over a wide range of flight conditions in the NACA Lewis altitude wind tunnel. A study was made of all these data and windmilling performance of gas turbine engines was generalized. Although internal-drag, air-flow, and total-pressure-drop parameters were generalized to a single curve for both the axial-flow type engines and another for the centrifugal-flow engine.
Date: December 12, 1951
Creator: Wallner, Lewis E. & Welna, Henry J.
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