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open access

Present status of polonium tolerance estimations

Description: This report contains a summary of biological information on distribution, excretion, and toxicity of polonium; a comparison of results obtained when maximum permissible exposure rates for man are calculated from available data by different methods; and a critical evaluation of the present status of Po tolerance estimates. A maximum permissible body content of the order of 0.2 {mu}c/70 Kg man is obtained by two methods. Applying an urinary excretion rate of 0.1% of body content/day, effective ha… more
Date: October 14, 1948
Creator: Hursh, J.B. & Stannard, J.N.
open access

Present status of research on boundary-layer control

Description: Report presenting a survey of the present status of research on boundary-layer control and its possible applications in aeronautics. The applications considered include reduction of profile drag by the elimination of turbulent separation, increase of the maximum lift coefficient through control of separation, use of suction and blowing slots near the trailing edge of the airfoil as a means of lateral control, use of boundary-layer control as a means of increasing the efficiency of diffusers and… more
Date: January 12, 1949
Creator: von Doenhoff, Albert E. & Loftin, Laurence K., Jr.
open access

The Preservation of Fluorescence Standards

Description: Report discussing the practice of using methyl methacrylate as a coating for platinium dishes in fluorescence method of uranium analysis. The experimental procedure described in this report to evaluate this practice indicates that the sample would be sufficiently protected from contamination and would not need to be stored in a desiccator.
Date: February 15, 1946
Creator: Grotta, H. M.
open access

Pressure and Temperature Measurement in Supercharger Investigations

Description: "With the further development of the supercharger, requirements with regard to measuring accuracy increase while at the same time the conditions under which the measurements must be carried out become more difficult. The present paper is a contribution toward the improvement and refinement of the measuring methods. For pressure measurements some suggestions are made with regard to design and location of the measuring stations" (p. 1).
Date: September 1940
Creator: Franz, A.
open access

Pressure available for cooling with cowling flaps

Description: Report presents the results of a full-scale investigation conducted in the NACA 20-foot tunnel to determine the pressure difference available for cooling with cowling flaps. The flaps were applied to an exit slot of smooth contour at 0 degree flap angle. Flap angles of 0 degree, 15 degrees, and 30 degrees were tested. Two propellers were used; propeller c which has conventional round blade shanks and propeller f which has airfoil sections extending closer to the hub. The pressure available for … more
Date: May 9, 1940
Creator: Stickle, George W.; Naiman, Irven & Crigler, John L.
open access

Pressure-Distribution Data for the NACA 64(Sub 1)-012 and 64(Sub 1)A012 Airfoils at High Subsonic Mach Numbers

Description: "Pressure-distribution data of the NACA 64(sub 1)-012 and 64(sub 1)A012 airfoils have been analyzed to determine the effects of increasing the trailing-edge angle from 9 to 14 degrees. The primary effect of increasing the trailing-edge angle was to decrease the loading over the rear portion of the airfoil under lifting conditions. The differences in trailing-edge load increased with Mach number and lift coefficient" (p. 1).
Date: May 6, 1949
Creator: Humphreys, Milton D.
open access

Pressure Distribution in Nonuniform Two-Dimensional Flow

Description: In an attempt to follow the time rate of change of the processes in turbulent flows by quantitative measurements the measurement of the pressure is often beset with insuperable difficulties for the reason that the speeds and hence the pressures to be measured are often very small. On the other hand, the measurement of very small pressures requires, at least, considerable time, so that the follow-up of periodically varying processes is as goad as impossible. In order to obviate these difficultie… more
Date: January 1943
Creator: Schwabe, M.
open access

Pressure-distribution investigation of an NACA 0009 airfoil with an 80-percent-chord plain flap and three tabs

Description: Pressure-distribution tests of an NACA 0009 airfoil with an 80-percent-chord plain flap and three plain tabs, having chord of 10, 20, and 30 percent of the flap chord, were made. Section data suitable for application to the design of horizontal and vertical tail surfaces were obtained. Resultant-pressure diagrams for the airfoil with the flap and the 20-percent-chord tab are presented. Plots are also given of increments of normal-force and hinge-moment coefficients for the airfoil, the flap, an… more
Date: May 1940
Creator: Ames, Milton B., Jr. & Sears, Richard I.
open access

Pressure-distribution investigation on an NACA 0009 airfoil with a 30-percent-chord plain flap and three tabs

Description: From Summary: "Pressure-distribution tests of an NACA 0009 airfoil with a 30-percent-chord plain flap and three plain tabs, having chords 10, 20, and 30 percent of the flap chord, were made. The purpose of these tests was to continue an investigation to supply structural and aerodynamic section data that may be applied to the design of horizontal and vertical tail surfaces. The results are presented as diagrams of resultant pressures and of resultant-pressure increments for the airfoil with the… more
Date: May 1940
Creator: Ames, Milton B., Jr. & Sears, Richard I.
open access

Pressure Distribution Measurements at High Speed and Oblique Incidence of Flow

Description: "The present report contains the results of a series of observations obtained for a wing of symmetrical profile for different angles of yaw. The shock tunnel with 0.4m x 0.4m cross section, of the Institute for Gas Dynamics at L.F.A. - Braunchweig was available for this work. The profile used was a 9 percent, thick hyperbolic profile with maximum thickness 40 percent aft, which was calculated by the method of F. Ringleb (2). Since the conformal transformation of this profile is known, the theor… more
Date: March 1947
Creator: Lippisch, A. & Beuschausen, W.
open access

Pressure-Distribution Measurements of a Low-Drag Airfoil With Slotted Flap Submitted by Curtiss-Wright Corporation

Description: "Pressure-distribution measurements were made at the request of the Materiel Division, U.S. Army Air Corps, on a 24-inch-chord wooden model equipped with a slotted flap and submitted by the Curtiss-Wright Corporation. The tests were made in the Langley two-dimensional tunnel at a Reynolds number of about 5,600,000" (p. 1).
Date: December 1941
Creator: Abbott, Ira H.
open access

Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation

Description: Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000.
Date: January 1942
Creator: Abbott, Ira H.
open access

Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane

Description: Report presenting pressure distribution measurements on two 24-inch chord models equipped with Fowler flaps in the two-dimensional low-turbulence pressure tunnel. Results regarding pressure-distribution diagrams and normal-force and moment coefficients are provided.
Date: January 1942
Creator: Abbott, Ira H.
open access

Pressure-distribution measurements on a full-scale horizontal tail surface for a Mach number range of 0.20 to 0.70

Description: Report presenting testing of a full-scale, semispan, horizontal tail surface for a jet-propelled fighter airplane in the 16-foot high-speed tunnel to determine the variation of the chordwise and spanwise pressure distributions with Mach number. Surface irregularities were found to cause appreciable distortion of the pressure distribution. Results regarding chordwise distributions, spanwise distribution, effect of Mach number on root bending moment, and estimated critical Mach numbers are provid… more
Date: June 25, 1947
Creator: Schueller, Carl F.
open access

Pressure-Distribution Measurements on a Straight and on a 35 Degree Swept-Back Tapered Wing

Description: "The spanwise lift-distribution measurements in straight air flow on a straight and a 35 deg swept-back tapered wing (NACA airfoil section 0012) are compared with theory for two angles of attack each (alpha approx. 6 deg and alpha approx. 12 deg) in the unstalled range of flow. The complete pressure distribution for the greater of the two angles is indicated" (p. 1).
Date: January 1947
Creator: Thiel, A. & Weissinger, J.
open access

Pressure Distribution Measurements on a Turbine Rotor Blade Passing Behind a Turbine Nozzle Lattice

Description: "As a turbine rotor turns, the blades traverse the wake zones of the nozzle vanes. A periodic fluctuation of the pressure distribution around the circumference of the rotor blade is therefore caused. It was desired to investigate quantitatively this effect. At the same time, the magnitude of the force acting upon one profile of the rotor-blade lattice at various positions of this lattice relative to the nozzle lattice was to be determined" (p. 1).
Date: September 1947
Creator: Hausenblas
open access

Pressure-distribution measurements on the rotating blades of a single-stage axial-flow compressor

Description: Investigation of the pressure distribution about the mean-radius section of the rotating blades of a single-stage axial-flow compressor at a blade Mach number of 0.35. The results indicated that the maximum suction pressure for thin low-camber rotor blades was only slightly greater than for the isolated airfoil of the same section. Results regarding the performance of the compressor, performance of the pressure-transfer device, pressure distribution, critical Mach number, and lift characteristi… more
Date: February 1947
Creator: Runckel, Jack F. & Davey, Richard S.
open access

Pressure-Distribution Measurements on the Tail Surfaces of a Rotating Model of the Design BFW - M31

Description: In order to obtain insight into the flow conditions on tail surfaces on airplanes during spins, pressure-distribution measurements were performed on a rotating model of the design BFW-M31. For the time being, the tests were made for only one angle of attack (alpha = 60 degrees) and various angles of yaw and rudder angles. The results of these measurements are given; the construction of the model, and the test arrangement used are described. Measurements to be performed later and alterations pla… more
Date: December 1949
Creator: Kohler, M. & Mautz, W.
open access

Pressure-Distribution Measurements on Unyawed Swept-Back Wings

Description: "This report presents comprehensive pressure-distribution measurements on four (4) swept-back wings (phi = 0 deg, 15 deg, 30 deg, and 45 deg) of constant chord and over a large range of angles of attack with symmetrical air flow. The distributions, experimentally obtained, were compared with theoretical ones calculated by the methods of Weissinger and Multhopp" (p. 1).
Date: July 1947
Creator: Jacobs, W.
open access

Pressure-distribution measurements over an extensible leading-edge flap on two wings having leading-edge sweep of 42 degrees and 52 degrees

Description: Report presenting an investigation of the pressure distribution over a leading-edge flap in the 19-foot pressure tunnel. Testing occurred on 42 degree and 52 degree sweptback wings of NACA 64(sub 1)-112 sections, with the 42 degree wing being used in conjunction with a circular cross-section fuselage in a high-wing combination.
Date: March 7, 1949
Creator: Salmi, Reino J.
open access

Pressure Distribution on the Fuselage of a Midwing Airplane Model at High Speeds

Description: Report presenting the pressure distribution on the fuselage of a midwing airplane model measured in the 8-foot high-speed wind tunnel at a range of speeds and lift coefficients. The primary purpose of the investigation was to provide data showing the air pressures on various parts of the fuselage for use in structural design.
Date: February 1943
Creator: Delano, James B.
open access

Pressure Distribution on Wings in Reversed Flow

Description: "The series of pressure distribution measurements at three test sections on NACA airfoils 2212 and M6 within 170 to 210 angles of attack in reversed flow proved to be largely independent of the profile form. In contradiction to the pressure distribution in normal flow considerable negative pressure from the upper surface spills over onto the lower surface, and vice versa, even in the zone of sound flow. The results are presented as chord-wise pressure and load distribution" (p. 1).
Date: April 1942
Creator: Naumann, A.
open access

Pressure distribution over a plug-type spoiler-slot aileron on a tapered wing with full span slotted flaps

Description: From Summary: "A pressure-distribution investigation was made in the Langley 7- by 10-foot tunnel of a plug-type spoiler-slot aileron on a semispan tapered-wing model of a typical fighter airplane equipped with full-span slotted flaps. The results of the investigation indicate peak pressure on a plug-type spoiler-slot aileron that may result in a compressibility shock on the plug aileron at high speed. The maximum loads on the plug aileron occurred in the high-speed condition for maximum up ail… more
Date: June 1946
Creator: Lowry, John G. & Turner, Thomas R.
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