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A method for determining the rate of heat transfer from a wing or streamline body

Description: From Summary: "A method for calculating the rate of heat transfer from the surface of an airfoil or streamline body is presented. A comparison with the results of an experimental investigation indicates that the accuracy of the method is good. This method may be used to calculate the heat supply necessary for heat de-icing or in ascertaining the heat loss from the fuselage of an aircraft operating at great altitude, for example."
Date: December 1942
Creator: Frick, Charles W., Jr. & McCullough, George B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of a Thermal Ice-Prevention System for a Wing Leading-Edge Landing-Light Installation

Description: Report discussing the creation of a thermal ice-prevention system of a bomber-type airplane to provide protection against ice and fog formations on the transparent fairing over the landing light in the wing leading edge. A comparison between the design performance and actual performance showed that the outer-surface heat-transfer coefficient was correctly predicted, but the inner-surface heat-transfer coefficient was four times as large, leading to failure of the plastic fairing.
Date: December 1944
Creator: Hillendahl, Wesley H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Performance of an exhaust-gas "blowdown" turbine on a nine-cylinder radial engine

Description: Report presenting tests on an exhaust-gas turbine with four separate nozzle boxes each covering a 90 degree arc of the nozzle diaphragm and each connected to a pair of adjacent cylinders in a Pratt & Whitney R-1340-12 nine-cylinder radial engine. Results regarding the power output of the engine and turbine, effect of the turbine on engine power, turbine power output and speed characteristics, mean turbine efficiency, effect of the blowdown turbine on exhaust-gas temperature, and condition of th… more
Date: December 1944
Creator: Turner, L. Richard & Desmon, Leland G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A method for calculating heat transfer in the laminar flow region of bodies

Description: Report presenting a practical method for determining the chordwise distribution of the rate of heat transfer from the surface of a wing or body of revolution to air. The method is limited to use to the determination of heat transfer fro the forward section of such bodies when the flow is laminar.
Date: December 1942
Creator: Allen, H. Julian & Look, Bonne C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wall interference in a two-dimensional-flow wind tunnel with consideration of the effect of compressibility

Description: Report presenting tunnel-wall corrections for an airfoil of finite thickness and camber in a two-dimensional-flow wind tunnel. The theory takes account of the effects of the wake of the airfoil and of the compressibility of the fluid and is based on the assumption that the chord of the airfoil is small in comparison with the height of the tunnel. The theoretical results are compared with the small amount of low-speed experimental data available and agreement is seen to be satisfactory, even for… more
Date: December 1944
Creator: Allen, H. Julian & Vincenti, Walter G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Control-Surface Characteristics 15: Various Contour Modifications of a 0.30-Airfoil-Chord Plain Flap on an NACA 66(215)-014 Airfoil

Description: Report presenting force-test measurements in two-dimensional flow made in the 4- by 6-foot vertical tunnel to determine the aerodynamic characteristics of an NACA 66(215)-014 airfoil equipped with true-contour, straight-contour, and beveled-trailing-edge flaps with chords 30 percent of the airfoil chord. The results are presented in the form of aerodynamic section characteristics for several flap deflections and for a sealed and unsealed gap at the flap nose.
Date: December 1943
Creator: Purser, Paul E. & Riebe, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of an NACA 23012 Airfoil With a 0.30-Airfoil-Chord Double Slotted Flap

Description: Report discusses the results of testing of flap position and deflection on the aerodynamic characteristics of a NACA 23012 airfoil with a double slotted flap with a chord 30 percent of the airfoil chord. The maximum lift coefficient, profile-drag coefficients, pitching-moment coefficients, lift, and drag are provided at several positions of the flap. The results were also compared to previous testing on several flap configurations.
Date: December 1943
Creator: Purser, Paul E.; Fischel, Jack & Riebe, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure distribution over an airfoil with a balanced split flap

Description: Report presenting a pressure-distribution investigation conducted in the 4- by 6-foot vertical wind tunnel to determine the air loads on an airfoil with a 22.1-percent-chord balanced split flap. Results regarding section pressure distribution and aerodynamic section coefficients are provided.
Date: December 1941
Creator: Lowry, John G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of a Spoiler-Slot Aileron on an NACA 23012 Airfoil With a Full-Span Fowler Flap

Description: Report presenting an investigation of a spoiler-slot aileron on an NACA 23012 airfoil with a full-span 30-percent-chord Fowler flap. The static rolling, yawing, and hinge moments were determined for several angles of attack and flap deflections. The ineffective region could be eliminated by a provision in the aileron linkage that would automatically uprig the ailerons as the flap is deflected.
Date: December 1941
Creator: Rogallo, F. M. & Spano, Bartholomew S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of 20-percent-chord plain and Frise ailerons on an NACA 23012 airfoil

Description: Report presenting an investigation of several modifications of 20-percent-chord plain and Frise ailerons on an NACA 23012 airfoil in the 7- by 10-foot wind tunnel. Static rolling, yawing, and hinge moments were determined for several angles of attack.
Date: December 1941
Creator: Purser, Paul E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind Tunnel Investigation of the Effects of Slot Shape and Flap Location on the Characteristics of a Low-Drag Airfoil Equipped with a 0.25-Chord Slotted Flap

Description: Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment measurements throughout useful angle of attack range for constant flap deflection and position of a low-drag airfoil. Two slots were investigated and practical flap paths were selected for each Slot shape had a negligible effect on the maximum lift coefficient flap deflected, the rounded-entry slot had lower profile drag.
Date: December 1944
Creator: Holtzclaw, Ralph W. & Weisman, Yale
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Limitations of lifting-line theory for estimation of aileron hinge-moment characteristics

Description: Report presenting hinge-moment parameters for several typical ailerons, which were calculated from section data with the aspect-ratio correlation as usually determined from lifting-line theory. The calculations showed that the agreement between experimental and calculated results was unsatisfactory.
Date: December 1943
Creator: Swanson, Robert S. & Gillis, Clarence L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of beveled-trailing-edge elevators on a typical pursuit fuselage at altitudes simulating-normal flight and spin conditions

Description: Report presenting lift and elevator hinge-moment characteristics were measured on horizontal tail provided with elevators having three different beveled trailing edges. Results regarding fuselage alone and fuselage interference, lift characteristics of fuselage-tail combination, elevator hinge-moment characteristics, drag, and comparison with data from two-dimensional-flow tests are provided.
Date: December 1942
Creator: Gillis, Clarence L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Systematic Model Experiments of the Bow-Spray Characteristics of Flying-Boat Hulls Operating at Low Speeds in Waves

Description: Report discusses the results of testing on several models of flying boats, the XPB2M-1, the XPBB-1, the JRM-1, and 11 other models to determine the effect of bow form on the amount of spray thrown onto the windshield of a flying boat in rough water. Several recommendations for reducing the height and volume of spray are provided. Any change in the hull form that softens the impact between the hull and waves seems to reduce the spray.
Date: December 1943
Creator: Locke, F. W. S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Various Surface Conditions on Press Fits of Steel Bushings and 17S-T Aluminum-Alloy Fittings

Description: Report presenting testing of specimens of 17S-T aluminum-alloy fittings with pressed-in steel bushings for various surface conditions. The surface conditions tested included bare surfaces, aonidcal coating and steel cadmium-plate, and one surface treated and the other bare, both without lubrication and with Gredag No. 83 as a lubricant. The calculated coefficients of friction for the various press fits for the investigation ranged from 0.33 for the unlubricated contact of bare steel and aluminu… more
Date: December 1942
Creator: Hartmann, E. C. & Reedy, J. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Aircraft Heaters 6: Heat Transfer Equations for the Single Pass Longitudinal Exchanger

Description: Report presenting an analysis of parallel flow and contraflow single pass heat exchangers, together with charts which allow the direct evaluation of the thermal performance of the units without recourse to trail-and-error techniques. The use of equations and charts is illustrated by several examples.
Date: December 1942
Creator: Martinelli, R. C.; Morrin, E. H. & Boelter, L. M. K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Preliminary Investigation of the Characteristics of Air Scoops on a Fuselage

Description: Report presenting an investigation of the characteristics of air scoops in the NACA propeller-research tunnel. The investigation showed that, at inlet-velocity ratios equal to or greater than 0.3, scoops in a forward position on the fuselage gave total pressures in the inlet nearly equal to free-stream total pressure.
Date: December 1942
Creator: Bell, E. Barton & DeKoster, Lucas J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Aircraft Heaters 5: Theory and Use of Heat Meters for the Measurement of Rates of Heat Transfer Which Are Independent of Time

Description: Report presenting a description of a meter which will measure the heat flowing through surfaces. Its operation is based on the measurement of the temperature decrease through a fixed thermal resistance. Only the case of heat flow independent of time is discussed in this particular report.
Date: December 1942
Creator: Martinelli, R. C.; Morrin, E. H. & Boelter, L. M. K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effect of concentrated loads on flexible rings in circular shells

Description: Report presenting a method of making strain measurements on a series of circular cylinders with reinforcing rings, subjected to concentrated loads, in which the bending stiffness of the rings was varied systematically over a wide range. Results regarding the general remarks, bending-moment coefficient, and skin shear coefficients are provided.
Date: December 1945
Creator: Kuhn, Paul; Duberg, John E. & Griffith, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight tests of beveled-trailing-edge ailerons with various modifications on a North American XP-51 airplane (AAF No.41-38)

Description: Report presenting flight testing using a North American XP-51 airplane with several arrangements of beveled-trailing-edge ailerons to determine the most satisfactory arrangement. Results regarding the aileron configuration, trimming tabs, and factors affecting symmetry of aileron characteristics are provided.
Date: December 1943
Creator: White, Maurice D. & Hoover, Herbert H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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