You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Results 15361 - 15384 of 19,853
  |   |  
Wind-tunnel investigation of wing ducts on a single engine pursuit airplane

Wind-tunnel investigation of wing ducts on a single engine pursuit airplane

Date: October 1, 1943
Creator: Czarnecki, K R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans

Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans

Date: October 1, 1943
Creator: Alexander, Sidney R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flying qualities of a twin-engine patrol airplane as estimated from wind-tunnel tests

Flying qualities of a twin-engine patrol airplane as estimated from wind-tunnel tests

Date: September 20, 1943
Creator: Mccullough, George B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
NACA Investigation of a Jet-Propulsion System Applicable to Flight

NACA Investigation of a Jet-Propulsion System Applicable to Flight

Date: September 17, 1943
Creator: Ellis, Macon C. & Brown, Clinton E.
Description: Following a brief history of the NACA investigation of jet propulsion, a discussion is given of the general investigation and analysis leading to the construction of the jet-propulsion ground-test mock-up. The results of burning experiments and of test measurements designed to allow quantitative flight performance predictions of the system are presented and correlated with calculations. These calculations are then used to determine the performance of the system on the ground and in the air at various speeds and altitudes under various burning conditions. The application of the system to an experimental airplane is described and some performance predictions for this airplane are made.
Contributing Partner: UNT Libraries Government Documents Department
Requirements for auxiliary stiffeners attached to panels under combined compression and shear

Requirements for auxiliary stiffeners attached to panels under combined compression and shear

Date: September 16, 1943
Creator: Scott, Merit & Weber, Robert L
Description: Panels of aluminum alloy sheets, framed by side and end stiffeners, were subjected to combined loading by means of offset knife edges applying loads to top and bottom end plates with reacting forces against the end plates supplied by laterally acting rollers. The test specimens were 17S-T aluminum alloy shoots 0.040 inch thick in panels of 10-inch width and three different lengths (approximately 10, 26, and 30 inch). Data were obtained for the bowing of transverse and longitudinal ribs of rectangular cross section and varying depths mounted on one side of the sheet only, for several ratios of compression to shear loads. Limiting values of the moments of inertia were calculated from these measurements. The experimental values exceed the theoretical values given by Timoshenko for the case of simply supported sheets with uniformly distributed boundary stresses. The work reported includes measurements of the effective shear moduli of the nine test panels with and without ribs. These data are compared with values published by Lahdo and Wagner.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic and hydrodynamic tests of a family of models of flying-boat hulls derived from a streamline body : NACA model 84 series

Aerodynamic and hydrodynamic tests of a family of models of flying-boat hulls derived from a streamline body : NACA model 84 series

Date: September 1943
Creator: Luoma, Arvo A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An approximate method of shear-lag analysis for beams loaded at right angles to the plane of symmetry of the cross section

An approximate method of shear-lag analysis for beams loaded at right angles to the plane of symmetry of the cross section

Date: September 1, 1943
Creator: Brilmyer, Harold J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculated and measured turning performance of a Navy F2A-3 airplane as affected by the use of flaps

Calculated and measured turning performance of a Navy F2A-3 airplane as affected by the use of flaps

Date: September 1, 1943
Creator: Kauffman, William M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Critical compressive stress for curved sheet supported along all edges and elastically restrained against rotation along the unloaded edges

Critical compressive stress for curved sheet supported along all edges and elastically restrained against rotation along the unloaded edges

Date: September 1, 1943
Creator: Stowell, Elbridge Z
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The effect of xylidines on the load-carrying capacity of an aircraft engine oil II

The effect of xylidines on the load-carrying capacity of an aircraft engine oil II

Date: September 1, 1943
Creator: Spurr, Robert A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of mean-line loading on the aerodynamic characteristics of some low-drag airfoils

Effects of mean-line loading on the aerodynamic characteristics of some low-drag airfoils

Date: September 1, 1943
Creator: Turner, Harold R , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
General porpoising tests on flying-boat-hull models

General porpoising tests on flying-boat-hull models

Date: September 1943
Creator: Locke, F W S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Heat Transfer Through Turbulent Friction Layers

Heat Transfer Through Turbulent Friction Layers

Date: September 1, 1943
Creator: Reichardt, H.
Description: The "general Prandtl number" Pr(exp 1) - A(sub q)/A Pr, aside from the Reynolds number determines the ratio of turbulent to molecular heat transfer, and the temperature distribution in turbulent friction layers. A(sub q) = exchange coefficient for heat; A = exchange coefficient for momentum transfer. A formula is derived from the equation defining the general Prandtl number which describes the temperature as a function of the velocity. For fully developed thermal boundary layers all questions relating to heat transfer to and from incompressible fluids can be treated in a simple manner if the ratio of the turbulent shear stress to the total stress T(sub t)/T in the layers near the wall is known, and if the A(sub q)/A can be regarded as independent of the distance from the wall. The velocity distribution across a flat smooth channel and deep into the laminar sublayer was measured for isothermal flow to establish the shear stress ratio T(sub t)/T and to extend the universal wall friction law. The values of T(sub t)/T which resulted from these measurements can be approximately represented by a linear function of the velocity in the laminar-turbulent transition zone. The effect of the temperature relationship of the material ...
Contributing Partner: UNT Libraries Government Documents Department
Magnolia Oil Field, Columbia County, Arkansas: Part 1. Petroleum-Engineering Study; Part 2. Derivation and Application of Material-Balance Equations

Magnolia Oil Field, Columbia County, Arkansas: Part 1. Petroleum-Engineering Study; Part 2. Derivation and Application of Material-Balance Equations

Date: September 1943
Creator: Carpenter, Charles B.; Schroeder, H. J. & Cook, Alton B.
Description: Report issued by the U.S. Bureau of Mines on studies conducted at the Magnolia oil fields in Columbia County, Arkansas. History, geology, and methods are presented. This report includes tables, graphs, maps, and illustrations.
Contributing Partner: UNT Libraries Government Documents Department
Measurements of the flying qualities of a Bell P-39D-1 airplane (AAF NO. 41-28378)

Measurements of the flying qualities of a Bell P-39D-1 airplane (AAF NO. 41-28378)

Date: September 1, 1943
Creator: Hoover, H H
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Notes on the effect of surface distortions on the drag and critical Mach number of airfoils

Notes on the effect of surface distortions on the drag and critical Mach number of airfoils

Date: September 1, 1943
Creator: Allen, J.
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Notes on the skipping of seaplanes

Notes on the skipping of seaplanes

Date: September 1, 1943
Creator: Parkinson, John B
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Periodic Heat Transfer at Small Pressure Fluctuations

Periodic Heat Transfer at Small Pressure Fluctuations

Date: September 1, 1943
Creator: Pfriem, H.
Description: The effect of cyclic gas pressure variations on the periodic heat transfer at a flat wall is theoretically analyzed and the differential equation describing the process and its solution for relatively. Small pressure fluctuations developed, thus explaining the periodic heat cycle between gas and wall surface. The processes for pure harmonic pressure and temperature oscillations, respectively, in the gas space are described by means of a constant heat transfer coefficient and the equally constant phase angle between the appearance of the maximum values of the pressure and heat flow most conveniently expressed mathematically in the form of a complex heat transfer coefficient. Any cyclic pressure oscillations, can be reduced by Fourier analysis to harmonic oscillations, which result in specific, mutual relationships of heat-transfer coefficients and phase angles for the different harmonics.
Contributing Partner: UNT Libraries Government Documents Department
Protection of nonmetallic aircraft from lighting I : general analysis

Protection of nonmetallic aircraft from lighting I : general analysis

Date: September 1, 1943
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Representative operating charts of propellers tested in the NACA 20-foot propeller-research tunnel

Representative operating charts of propellers tested in the NACA 20-foot propeller-research tunnel

Date: September 1, 1943
Creator: Gray, W H & Mastrocola, Nicholas
Description: Report presents the results of tests of full-scale propellers made in the 20-foot propeller-research tunnel (PRT) at the Langley Memorial Aeronautical Laboratory. The power coefficients of all dual-rotating propellers in the report represent the sum of the power coefficients of the front and rear propellers and are for the test conditions in which blade angles of the front and rear propellers were set to absorb approximately equal power at peak efficiency only.
Contributing Partner: UNT Libraries Government Documents Department
Some analyses of systematic experiments on the resistance and porpoising characteristics of flying-boat hulls

Some analyses of systematic experiments on the resistance and porpoising characteristics of flying-boat hulls

Date: September 1, 1943
Creator: Locke, F W S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some lift and drag measurements of two configurations of a nacelle and oil-cooler scoop for the Hughes-Kaiser cargo airplane

Some lift and drag measurements of two configurations of a nacelle and oil-cooler scoop for the Hughes-Kaiser cargo airplane

Date: September 1, 1943
Creator: Quinn, John H , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Some notes on the determination of the stick-fixed neutral point from wind-tunnel data

Some notes on the determination of the stick-fixed neutral point from wind-tunnel data

Date: September 1, 1943
Creator: Schuldenfrei, Marvin
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The strength of thin-wall cylinders of D cross section in combined pure bending and torsion

The strength of thin-wall cylinders of D cross section in combined pure bending and torsion

Date: September 1, 1943
Creator: Sherwood, A W
Description: The results of tests of 56 cylinders of D cross section conducted in the Aeronautical Laboratory of the University of Maryland are presented in this report. These cylinders were subjected to pure bending and torsional moments of varying proportions to give the strength under combined loading conditions. The average buckling stress of these cylinders has been related to that of circumscribing circular cylinders for conditions of pure torsion and pure bending and the equation of the interaction curve has been determined for conditions of combined loading.
Contributing Partner: UNT Libraries Government Documents Department