National Advisory Committee for Aeronautics (NACA) - 13 Matching Results

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Analysis of spanwise temperature distribution in three types of air-cooled turbine blade

Description: From Summary: An approximate method for determining the allowable stress-limited blade-temperature distribution is included, with brief accounts of a method for determining the maximum allowable effective gas temperatures and the cooling-air requirements. Numerical examples that illustrate the use of the various temperature-distribution equations and of the nondimensional charts are also included.
Date: March 1, 1950
Creator: Livingood, John N. B. & Brown, W. Byron
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of thrust augmentation of turbojet engines by water injection at compressor inlet including charts for calculating compression processes with water injection

Description: From Summary: "Curves are presented that show the theoretical performance of the augmentation method for various amounts of water injected and the effects of varying flight Mach number, altitude, ambient-air temperature, ambient relative humidity, compressor pressure ratio, and inlet-diffuser efficiency. Numerical examples, illustrating the use of the psychrometric chart and the Mollier diagram in calculating both compressor-inlet and compressor-outlet conditions when water is injected at the c… more
Date: June 1, 1950
Creator: Wilcox, E. Clinton & Trout, Arthur M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Compressible Laminar Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient

Description: "An approximate method for the calculation of the compressible laminar boundary layer with heat transfer and arbitrary pressure gradient, based on Thwaites' correlation concept, is presented. With the definition of dimensionless shear and heat-transfer parameters and an assumed correlation of these parameters in terms of a momentum parameter, a complete system of relations for calculating skin friction and heat transfer results. Knowledge of velocity or temperature profiles is not necessary in … more
Date: February 1, 1955
Creator: Cohen, Clarence B. & Reshotko, Eli
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Direct Measurements of Skin Friction

Description: "A device has been developed to measure local skin friction on a flat plate by measuring the force exerted upon a very small movable part of the surface of the flat plate. These forces, which range from about 1 milligram to about 100 milligrams, are measured by means of a reactance device. The apparatus was first applied to measurements in the low-speed range, both for laminar and turbulent boundary layers. The device was then applied to high-speed subsonic flow and the turbulent-skin-friction … more
Date: June 1, 1951
Creator: Dhawan, Satish
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Generalization of Boundary-Layer Momentum-Integral Equations to Three-Dimensional Flows Including Those of Rotating System

Description: "The Navier-Stokes equations of motion and the equation of continuity are transformed so as to apply to an orthogonal curvilinear coordinate system rotating with a uniform angular velocity about an arbitrary axis in space. A usual simplification of these equations as consistent with the accepted boundary-layer theory and an integration of these equations through the boundary layer result in boundary-layer momentum-integral equations for three-dimensional flows that are applicable to either rota… more
Date: November 1, 1950
Creator: Mager, Artur
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Resolution Autoradiography

Description: This investigation was made to adapt wet-process autoradiography to metallurgical samples to obtain high resolution of segregated radioactive elements in microstructures. Results are confined to development of the technique, which was perfected to a resolution of less than 10 microns. The radioactive samples included carbon-14 carburized iron and steel, nickel-63 electroplated samples, a powder product containing nickel-63, and tungsten-185 in N-155 alloy.
Date: June 1, 1953
Creator: Towe, George C.; Gomberg, Henry J. & Freemen, J. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of free-space oscillating pressures near propellers at flight Mach numbers to 0.72

Description: "In the course of a short flight program initiated to check the theory of Garrick and Watkins (NACA rep. 1198), a series of measurements at three stations were made of the oscillating pressures near a tapered-blade plan-form propeller and rectangular-blade plan form propeller at flight Mach numbers up to 0.72. In contradiction to the results for the propeller studied in NACA rep. 1198, the oscillating pressures in the plane ahead of the propeller were found to be higher than those immediately b… more
Date: July 1, 1958
Creator: Kurbjun, Max C. & Vogeley, Arthur W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Mechanism of Start and Development of Aircraft Crash Fires

Description: "Full-scale aircraft crashes were made to investigate the mechanism of the start and development of aircraft crash fires. The results are discussed herein. This investigation revealed the characteristics of the ignition sources, the manner in which the combustibles spread, the mechanism of the union of the combustibles and ignition sources, and the pertinent factors governing the development of a crash fire as observed in this program" (p. 547).
Date: August 1, 1952
Creator: Pinkel, I. Irving; Preston, G. Merritt & Pesman, Gerard J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Minimum-drag ducted and pointed bodies of revolution based on linearized supersonic theory

Description: The linearized drag integral for bodies of revolution at supersonic speeds is presented in a double-integral form which is not based on slender-body approximations but which reduces to the equal slender-body expression in the proper limit. With the aid of a suitably chosen auxiliary condition, the minimum-external-wave-drag problem is solved for a transition section connecting two semi-infinite cylinders. The projectile tip is a special case and is compared with the Von Karman projectile tip. C… more
Date: March 1, 1954
Creator: Parker, Hermon M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Relation Between Roughness of Interface and Adherence of Porcelain Enamel to Steel

Description: "Porcelain-enamel ground coats were prepared and applied under conditions that gave various degrees of adherence between enamel and a low-carbon steel (enameling iron). The variations in adherence were produced by (a) varying the amount of cobalt-oxide addition in the frit, (b) varying the type of metallic-oxide addition in the frit, keeping the amount constant at 0.8 weight percent, (c) varying the surface treatment of the metal before application of the enamel, by pickling, sandblasting, and … more
Date: October 1, 1952
Creator: Richmond, J. C.; Moore, D. G.; Kirkpatrick, H. B. & Harrison, W. N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A study of the zero-lift drag-rise characteristics of wing-body combinations near the speed of sound

Description: "Comparisons have been made of the shock phenomena and drag-rise increments for representative wing and central-body combinations with those for bodies of revolution having the same axial developments of cross-sectional areas normal to the airstream. On the basis of these comparisons, it is concluded that near the speed of sound the zero-lift drag rise of a low-aspect-ratio thin-wing and body combination is primarily dependent on the axial development of the cross-sectional areas normal to the … more
Date: August 1, 1952
Creator: Whitcomb, Richard T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical and Experimental Investigation of Additive Drag

Description: "The significance of additive drag is discussed and equations for determining its approximate value are derived for annular and open-nose inlets. Charts are presented giving values of additive drag coefficient over a range of free-stream Mach numbers for open and for annular-nose inlets with conical flow at the inlet. The effects on additive drag of variable inlet-total-pressure recovery and static pressures on the centerbody are investigated and an analytical method of predicting the variation… more
Date: February 1, 1951
Creator: Sibulkin, Merwin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Theoretical study of the transonic lift of a double-wedge profile with detached bow wave

Description: "A theoretical study is described of the aerodynamic characteristics at small angle of attack of a thin, double-wedge profile in the range of supersonic flight speed in which the bow wave is detached. The analysis is carried out within the framework of the transonic (nonlinear) small-disturbance theory, and the effects of angle of attack are regarded as a small perturbation on the flow previously calculated at zero angle. The mixed flow about the front half of the profile is calculated by relax… more
Date: August 1, 1952
Creator: Vincenti, Walter G. & Wagoner, Cleo B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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