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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.
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Pressure distribution measurements on various surfaces of a 0.2375-scale model of the Douglas XA-26 airplane in the 19-foot pressure tunnel

Description: Report presenting pressure-distribution measurements on a scale model of the Douglas XA-26 airplane as obtained in the 19-foot pressure tunnel. The measurements were made on the spinner-cowl-nacelle assembly and the fuselage for a range of angles of yaw and angles of attack.
Date: October 1943
Creator: Ashworth, C. Dixon
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.
open access

Pressure distribution over a sharp-nose body of revolution at transonic speeds by the NACA wing-flow method

Description: Report presenting an investigation to obtain the pressure distribution over a sharp-nose body of revolution with a circular-arc profile and fineness ratio 6 at transonic speeds using the NACA wing-flow method. Results regarding the variation of pressure coefficient with Mach number, pressure distributions along the body axis, pressure drag, and effects of interference and horizontal gradient are provided.
Date: March 5, 1948
Creator: Danforth, Edward C. B. & Johnston, J. Ford
open access

Pressure distribution over an NACA 23012 airfoil with a fixed slot and a slotted flap

Description: Report presents the results of a pressure-distribution investigation conducted in the Langley Memorial Aeronautical Laboratory 7 by 10-foot wind tunnel to determine the air loads on an NACA 23012 airfoil in combination with a fixed leading-edge slot and a slotted flap. Pressures were measured over the upper and lower surfaces of the component parts of the combination for several angles of attack and at several flap settings. The data, presented as pressure diagrams and graphs of section coeffic… more
Date: July 30, 1941
Creator: Harris, Thomas A. & Lowry, John G.
open access

Pressure distribution over NACA 23012 airfoil with a slotted and a split flap

Description: A pressure-distribution investigation has been conducted in the NACA 4 by 6-foot vertical wind tunnel to determine the air loads on an NACA 23012 airfoil in combination with a 25.66-percent-chord slotted flap and a 20-percent-chord split flap. Pressures were measured on both the upper and the lower surfaces of the main airfoil and the flaps for several angles of attack and at several flap settings. The data, presented as pressure diagrams and as graphs of the section coefficients for the flap a… more
Date: May 28, 1940
Creator: Harris, Thomas A. & Lowry, John G.
open access

Pressure Distributions and Force Tests of an NACA 65-210 Airfoil Section With a 50-Percent-Chord Flap

Description: Note presenting pressure distributions and force measurements in the two-dimensional low-turbulence pressure tunnel at low Mach numbers and high Reynolds numbers of an NACA 65-210 airfoil equipped with a 50-percent-chord plain flap. Tests were carried out for flap deflections of 0, 4, 7, and 10 degrees. These flap deflections provided considerably reduced drag coefficients at life coefficients above the design range of the plain airfoil.
Date: January 1947
Creator: Klein, Milton M.
open access

Pressure Distributions for Representative Airfoils and Related Profiles

Description: Note presenting selected pressure-distribution diagrams for a number of conventional and special airfoils. The conventional airfoils include the NACA 22, 44, and 230 series airfoils and Clark Y family and the special airfoils consist of circular-arc sections of several thicknesses and a number of synthetic airfoils. The pressure distributions are in most cases given for several lift coefficients including that at the ideal angle of attack.
Date: February 1946
Creator: Theodorsen, Theodore & Naiman, Irven
open access

Pressure Distributions on Thin Conical Body of Elliptic Cross Section at Mach Number 1.89

Description: Memorandum presenting an investigation conducted to determine the pressure distribution on a conical body of elliptic cross section at a Mach number of 1.89. Experimental data are presented for a range of angles of yaw from -16 to 16 degrees and angles of attack from -10 to 10 degrees. As the angle of flow deflection was increased, the deviation from experiment of the theoretical pressure distribution slightly increased, although agreement was satisfactory over the entire range of calculations.
Date: January 20, 1949
Creator: Maslen, Stephen H.
open access

Pressure Distributions Over a Wing-Fuselage Model at Mach Numbers of 0.4 to 0.99 and at 1.2

Description: Report presenting pressure distributions over a prolate spheroid of fineness ratio 6 and over a combination of this body with an NACA 65-010 wing section for a range of Mach numbers. Results regarding wall and sting interference, nature of flow over a model in the transonic region, development of supersonic flow from subsonic flow, and a comparison of experimental and theoretical flow at subsonic stream Mach numbers are provided.
Date: November 3, 1948
Creator: Matthews, Clarence W.
open access

Pressure-Drop Characteristics of Orifice Plates Used to Simulate Radiators

Description: Report presenting an investigation of the pressure-drop characteristics of orifice plates, which has been conducted to facilitate the design of resistances to simulate various types of cooling units. This use of the orifice plates was found to be practical because of the simple construction of the plates, the ease of which pressure drop can be varied by use of corks, and the absence of any large scale effects.
Date: March 1942
Creator: Czarnecki, K. R.
open access

Pressure Lag in Tubing Used in Flight Research

Description: "Tests described in this report were undertaken to obtain a quantitative measure of the pressure lag in typical pressure-tubing systems used by the Ames Aeronautical Laboratory in flight research investigations. Lag measurements were made with both single-direction and oscillating pressure changes. Single-direction pressure changes were investigated to determine if the lag in orifice-pressure lines and in the research airspeed and altitude measuring systems of pursuit-type airplane undergoing f… more
Date: July 1945
Creator: Turner, Howard L. & Rathert, George A., Jr.
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Pressure loss in ducts with compound elbows

Description: From Summary: "Results are presented of measurement of the pressure drop in ducts produced by two equal 90 degree elbows arranged at three different angular positions to each other, placed adjacent to each other, or separated by straight ducts of various lengths. The measured pressure drops have been analyzed and correlated, and the results are summarized in the form of curves adapted for design computations of pressure drop in compound-duct bends."
Date: February 1943
Creator: Weske, John R.
open access

Pressure recovery at supersonic speeds through annular duct inlets situated in a region of appreciable boundary layer 1: addition of energy to the boundary layer

Description: Report presenting a model with a nozzle upstream of an annular duct inlet for the purpose of ejecting high-velocity air into the boundary layer of the flow along the forebody tested between Mach numbers of 1.36 and 2.01. Results wind-tunnel data, equivalent pressure recovery, and scale effects are provided.
Date: April 1, 1948
Creator: Davis, Wallace F. & Brajnikoff, George B.
open access

Pressure Recovery at Supersonic Speeds Through Annular Duct Inlets Situated in a Region of Appreciable Boundary Layer 2: Effect of an Oblique Shock Wave Immediately Ahead of the Inlet

Description: Memorandum presenting an investigation of a model with a ramp that produced an oblique shock wave in front of an annular duct inlet, which was tested at Mach numbers between 1.36 and 2.01 to determine the effect of reducing the entrance Mach number on the total-pressure recovery after diffusion. The results showed that the maximum total-pressure recovery of the model investigated was considerably improved through the addition of a ramp.
Date: August 9, 1948
Creator: Brajnikoff, George B.
open access

Pressure Recovery for Missiles with Reaction Propulsion at High Supersonic Speeds (The Efficiency of Shock Diffusers)

Description: "The problem of the intake of air is treated for a missile flying at supersonic speeds and of changing the kinetic energy of the air into pressure with the least possible losses. Calculations are carried out concerning the results which can be attained. After a discussion of several preliminary experiments, the practical solution of the problem at hand is indicated by model experiments. The results proved very satisfactory in view of the results which had been attained previously and the values… more
Date: June 1947
Creator: Oswatitsch, K.
open access

Pressure-sensitive system for gas-temperature control

Description: From Summary: "A thermodynamic relation is derived and simplified for use as a temperature-limiting control equation involving measurement of gas temperature before combustion and gas pressures before and after combustion. For critical flow in the turbine nozzles of gas-turbine engines, the control equation is further simplified to require only measurements upstream of the burner. Hypothetical control systems are discussed to illustrate application of the control equations."
Date: March 4, 1948
Creator: Cesaro, Richard S. & Matz, Norman
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