UNT Libraries Government Documents Department - 14 Matching Results

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Construction of Finned Aluminum Muffs for Aircraft Engine Cylinder Barrels

Description: "This report describes the material, cutting-tool development, and machining procedure used in constructing an air-cooled cylinder barrel having a cooling muff with 2-inch fins spaced 1/8 inch. Details of two types of thread form used for the barrel to head assembly with the cooling muff are also presented" (p. 1).
Date: April 1942
Creator: Langley Memorial Aeronautical Laboratory

The Effect of Spinner-Body Gap on the Pressures Available for Cooling in the NACA E-Type Cowling

Description: "Tests of a 1/3-scale model of an NACA E-type cowling were made in the 8-foot high-speed tunnel for the purpose of determining the effect of the gap between the skirt of the hollow spinner and the cowling proper on the pressures available for cooling. It was found that even a large gap (0.096 in. on the model) had no appreciable effect on the available cooling pressures" (p. 1).
Date: March 1943
Creator: Becker, John V. & Mattson, Axel T.

Interference effects of longitudinal flat plates on low-drag airfoils

Description: Three airfoils were tested with an intersecting flat plate normal to the span as a preliminary study of interference effects on airfoils. Small interference effects were noted on the first two airfoils, while larger effects were noted on the NACA 66,2-422 section, which had previously been shown to be unconservative with respect to separation. Airfoils known to be conservative should be used for inboard sections subject to nacelle and fuselage interference.
Date: November 1942
Creator: Abbott, Ira H.

Investigation of effects of various camouflage paints and painting procedures on the drag characteristics of an NACA 65(sub 421)-420, a = 1.0 airfoil section

Description: Report presenting an investigation of the effects of various camouflage paints and painting procedures on the drag characteristics of a low-drag airfoil in the two-dimensional low-turbulence pressure tunnel. While applying paint has generally been found to decrease smoothness and increase drag, the care taken in preparation and application of the paint seems to be the dominant influence on the drag. Testing occurred with several different types of paints and several different painting methods.
Date: July 1944
Creator: Braslow, Albert L.

Investigation of Extreme Leading-Edge Roughness on Thick Low-Drag Airfoils to Indicate Those Critical to Separation

Description: Bulletin presenting a study of several airfoils, including a conventional NACA 23021 and some low-drag airfoils for which the thickness had been increased, as smooth airfoils and after the application of a standard roughness. The results show some of the airfoils to be critical to separation resulting from such flow disturbances.
Date: June 1942
Creator: Davidson, Milton

Investigation of the Variation of Lift Coefficient With Reynolds Number at a Moderate Angle of Attack on a Low-Drag Airfoil

Description: Bulletin presenting an investigation of the boundary layer about the NACA 66,2-216, a = 0.6 airfoil section in the two-dimensional low-turbulence tunnel. The primary purpose was to find an explanation for the decreased slope of the lift curve observed for some of the low-drag sections outside the low-drag range at low Reynolds numbers.
Date: November 1942
Creator: von Doenhoff, Albert E. & Tetervin, Neal

Notes on the Effects of Trailing-Edge Shapes of Low-Drag Airfoils on Profile Drag and the Trim and Balance of Control Surfaces

Description: Report presenting measurements of drag, lift, and aileron hinge moments on a 100-inch-chord model with various modifications to the trailing edge of the 0.20c Frise type aileron. The purpose of the data is to show qualitatively the effects of comparatively small modifications to the trailing edge of an aileron.
Date: March 1942
Creator: Underwood, W. J.

A preliminary study of the effect of compressive load on the fairness of a low-drag wing specimen with Z-section stiffeners

Description: "A low-drag airfoil specimen was loaded in compression, and surveys of the fairness of the surface were made at different stresses as well as at zero load after successively higher stresses had been applied and removed. The tests reported and the discussion of the significance of the results obtained suggest a procedure for determining the probable outcome of a particular type of construction for a low-drag wing" (p. 1).
Date: January 1943
Creator: Jacobs, Eastman N.; Lundquist, Eugene E.; Davidson, Milton & Houbolt, John C.

Variation with Mach Number of Static and Total Pressures Through Various Screens

Description: Tests were conducted in the Langley 24-inch highspeed tunnel to ascertain the static-pressure and total-pressure losses through screens ranging in mesh from 3 to 12 wires per inch and in wire diameter from 0.023 to 0.041 inch. Data were obtained from a Mach number of approximately 0.20 up to the maximum (choking) Mach number obtainable for each screen. The results of this investigation indicate that the pressure losses increase with increasing Mach number until the choking Mach number, which can be computed, is reached. Since choking imposes a restriction on the mass rate of flow and maximum losses are incurred at this condition, great care must be taken in selecting the screen mesh and wire dimmeter for an installation so that the choking Mach number is.
Date: February 1, 1946
Creator: Adler, Alfred A.