National Advisory Committee for Aeronautics (NACA) - 7 Matching Results

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Fuel investigation in a tubular-type combustor of a turbojet engine

Description: A series of 11 fuels ranging in volatility and including various types of hydrocarbons were tested in a single tubular combustion chamber of a turbojet engine under inlet-air conditions simulating engine operation at two speeds at an altitude of 40,000 feet. Temperature-rise data at various fuel-air ratios were obtained for each set of air-flow conditions. Results regarding the effect of combustor inlet-air conditions on temperature rise, four different series of tests, and a review of some gen… more
Date: August 1, 1947
Creator: Tischler, Adelbert O. & Dittrich, Ralph T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An empirically derived method for calculating pressure distribution at supercritical Mach numbers and moderate angles of attack

Description: Report presenting a procedure for calculating pressure distributions over airfoils at supercritical Mach numbers. Only the forward portion of the airfoil, where interaction between local boundary-layer thickness and local-pressure distribution is negligible, is considered in detail. The method cannot be considered definitive because it requires that certain characteristics regarding pressure distributions and geometric properties be known.
Date: April 1, 1947
Creator: Nitzberg, Gerald E. & Sluder, Loma E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Velocity distributions on two-dimensional wing-duct inlets by conformal mapping

Description: The conformal-mapping method of the Cartesian mapping function is applied to the determination of the velocity distribution on arbitrary two-dimensional duct-inlet shapes such as are used in wing installations. An idealized form of the actual wing-duct inlet is analyzed. The effects of leading edge stagger, inlet-velocity ratio, and section lift coefficients on the velocity distribution are included in the analysis. Numerical examples are given and, in part, compared with experimental data.
Date: April 1, 1947
Creator: Perl, W. & Moses, H. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analysis of the Full-Floating Journal Bearing

Description: Report discussing an analysis of the operating characteristics of a full-floating journal bearing, a bearing in which a floating sleeve is located between the journal and bearing surfaces, is presented together with charts from which the performance of such bearings may be predicted.
Date: January 1, 1947
Creator: Shaw, M. C. & Nussdorfer, T. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099): Longitudinal-Stability and -Control Characteristics

Description: This report contains the flight-test results of the longitudinal-stability and -control phase of a general flying qualities investigation of the Lockheed P-80A airplane (Army No. 44-85099). The tests were conducted at indicated airspeeds up to 530 miles per hour (0.76 Mach number) at low altitude and up to 350 miles per hour (0.82) Mach number) at high altitude. These tests showed that the flying qualities of the airplane were in accordance with the requirements of the Army Air Forces Stability… more
Date: July 1, 1947
Creator: Anderson, Seth B.; Christofferson, Frank E. & Clousing, Lawrence A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cooling of Gas Turbines 6 - Computed Temperature Distribution Through Cross Section of Water-Cooled Turbine Blade

Description: "A theoretical analysis of the cross-sectional temperature distribution of a water-cooled turbine blade was made using the relaxation method to solve the differential equation derived from the analysis. The analysis was applied to specific turbine blade and the studies icluded investigations of the accuracy of simple methods to determine the temperature distribution along the mean line of the rear part of the blade, of the possible effect of varying the perimetric distribution of the hot gas-to… more
Date: May 1, 1947
Creator: Livingood, John N. B. & Sams, Eldon W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests of Rocket-Powered "Tin-Can" Models of AAF Project MX-800

Description: Flight tests were made of six noninstrumented rocket-powered "Tin Can" models of AAF Project MX-800. Velocity and drag data were obtained by use of CU Doppler radar. The existence of stability and adequate structural strength for flight near zero lift was checked by visual and photographic observation. Drag data obtained during the tests agreed reasonably well with estimates based on experimental data from NACA RM-2 rocket-powered drag research models.
Date: December 1, 1947
Creator: Purser, Paul E. & Stone, David G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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