National Advisory Committee for Aeronautics (NACA) - 198 Matching Results

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Tests on Stiffened Circular Cylinders

Description: "Compressive tests were made of two series of stiffened circular cylindrical shells under axial load. All the shells were 16 inches in diameter by 24 inches in length and were made of aluminum-alloy sheet curved to the proper radius and welded with one longitudinal weld. The ratios of diameter to thickness of shell wall in the two series of specimens were 258 and 572" (p. 1).
Date: March 1941
Creator: Holt, Marshall
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Round and Flat Spoilers on a Tapered Wing in the NACA 19-Foot Pressure Wind Tunnel

Description: "Several arrangements of round and flat spanwise spoilers attached to the upper surface of a tapered wing were tested in the NACA 19-foot pressure wind tunnel to determine the most effective type, location, and size of spoiler necessary to reduce greatly the lift on the wings of large flying boats when moored. The effect of the various spoilers on the lift, the drag, and the pitching-moment characteristics of the tapered wing was measured over a range of angles of attack from zero to maximum li… more
Date: March 1941
Creator: Wenzinger, Carl J. & Bowen, John D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of a gust-alleviating wing in the gust tunnel

Description: "Tests were made in the NACA gust tunnel to determine the effectiveness of a torsionally flexible wing with the torsion axis ahead of the locus of the section aerodynamic centers in reducing airplane accelerations due to atmospheric gusts. For three gust shapes, a series of flights was made with the airplane model equipped with either a torsionally flexible or a rigid wing. The results indicated that the torsionally flexible wing reduced the maximum acceleration increment 5 percent for the shar… more
Date: April 1941
Creator: Shufflebarger, C. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of Several Factors Affecting the Performance of a High-Speed Pursuit Airplane With Air-Cooled Radial Engine

Description: Report details an investigation into various potential improvements and modifications to pursuit airplanes. NACA low-drag airfoil sections and their use for reducing drag and increasing compressibility speeds were examined. Other items covered include the propeller slipstream, high-speed cowling arrangement, and placement of wing guns.
Date: November 1941
Creator: Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some effects of rainfall on flight of airplanes and on instrument indications

Description: "Several possible effects of heavy rain on the aerodynamic performance of an airplane and of heavy rain and associated atmospheric phenomena on the indications of flight instruments are briefly considered. It is concluded that the effects of heavy rain on the performance of an airplane are not so great as to force the airplane down from moderate altitudes. Serious malfunctioning of the air-speed indicator may occur, however, as a result of flooding of the pitot-static head and subsequent accumu… more
Date: April 1941
Creator: Rhode, Richard V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Aging on Mechanical Properties of Aluminum-Alloy Rivets

Description: "Curves and tabular data present the results of strength tests made during and after 2 1/2 years of aging on rivets and rivet wire of 3/16-inch nominal diameter. The specimens were of aluminum alloy: 24S, 17S, and A17S of the duralumin type and 53S of the magnesium-silicide type" (p. 1).
Date: April 1941
Creator: Roop, Frederick C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Model Tests of a Wing-Duct System for Auxiliary Air Supply

Description: Report discusses the design of a cooling system developed for a Pratt & Whitney H-2800 engine equipped with a two-stage supercharger. The wing-duct system was newly developed and was determined to be a valuable method for cooling engine auxiliaries by combining simplicity with low drag and excellent cooling capabilities.
Date: January 1941
Creator: Bierman, David & Corson, Blake W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Spin Tests of a Low-Wing Monoplane to Investigate Scale Effect in the Model Test Range

Description: "Concurrent tests were performed on a 1/16 and a 1/20 scale model (wing spans of 2.64 and 2.11 ft. respectively) of a modern low wing monoplane in the NACA 15 foot free-spinning wind tunnel. Results are presented in the form of charts that afford a direct comparison between the spins of the two models for a number of different conditions. Qualitatively, the same characteristic effects of control disposition, mass distribution, and dimensional modifications were indicated by both models" (p. 1).
Date: May 1941
Creator: Donlan, Charles J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Methods of analyzing wind-tunnel data for dynamic flight conditions

Description: The effects of power on the stability and the control characteristics of an airplane are discussed and methods of analysis are given for evaluating certain dynamic characteristics of the airplane that are not directly discernible from wind tunnel tests alone. Data are presented to show how the characteristics of a model tested in a wind tunnel are affected by power. The response of an airplane to a rolling and a yawing disturbance is discussed, particularly in regard to changes in wing dihedral… more
Date: July 22, 1941
Creator: Donlan, C. J. & Recant, I. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The theoretical lateral motions of an automatically controlled airplane subjected to a yawing moment disturbance

Description: Report presenting an investigation of the lateral motion resulting from a disturbance of the type produced by asymmetric loss of thrust for a hypothetical average airplane equipped with an automatic pilot. Plots of the resultant motion and various modes that constitute the motion are presented for fixed controls and for various amounts of autopilot.
Date: June 1941
Creator: Imlay, Frederick H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling and Performance Tests of a Continental A-75 Engine

Description: Note presenting an investigation to determine the performance of a small airplane with two Continental A-75 air-cooled engines enclosed in the wings. The object of the tests was to determine the quantity of air and the pressure difference required for satisfactory cooling of the engine at sea level and at altitude. The engine could be cooled satisfactorily at sea level with wide-open throttle and maximum-power mixture with a pressure difference of 4.5 inches of water and 1.06 pounds of cooling … more
Date: July 1941
Creator: Ellerbrock, Herman H., Jr. & Bullock, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Tensile Elastic Properties at Low Temperatures of 18:8 Cr-Ni Steel as Affected by Heat Treatment and Slight Plastic Deformation

Description: Note presenting the relationship between stress, strain, and permanent set for 18:8 Cr-Ni steel as measured at -110 degrees Fahrenheit. The influence of annealing and slight plastic extension upon the derived elastic properties is also discussed.
Date: July 1941
Creator: Mebs, R. W. & McAdam, D. J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Minimum Induced Drag in Wing-Fuselage Interference

Description: Note presenting a method for obtaining the minimum induced drag of airfoils in the proximity of ideal internal boundaries. The theorem is applied to the case of an ideal wing-fuselage combination consisting of a lifting line intersecting an infinitely long circular cylindrical fuselage to determine the effect of wing height on the minimum induced drag. The analysis used can be modified for combinations with different fuselage cross sections.
Date: September 1941
Creator: Pepper, Perry A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling Effects of an Airplane Equipped With an NACA Cowling and a Wing-Duct Cooling System

Description: Report presenting cooling tests of a Northrop A-17A attack airplane equipped with a conventional NACA cowling and then with a wing-duct cooling system. Ground cooling for the wing-duct system without cowl flap was better than for the cowling with flap, but was improved by installing a cowl flap. Satisfactory temperatures were maintained in climb and high-speed flight, but a greater quantity of cooling air was needed for the wing-duct system.
Date: June 1941
Creator: Turner, L. I., Jr.; Bierman, David & Boothby, W. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Stability and Control Tests in the NACA Free-Flight Wind Tunnel and Correlation With Full-Scale Flight Tests

Description: Note presenting a study of stability and control of airplanes by means of dynamic scale models in the 12-foot free-flight wind tunnel. Tests of a scale model of the F-36A airplane were used to develop the testing technique and to afford a comparison of tests of a model in the tunnel with flight tests of the corresponding airplane. Results regarding longitudinal stability and control and lateral stability and control are provided.
Date: June 1941
Creator: Shortal, Joseph A. & Osterhout, Clayton J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Methods of Testing on the Ultimate Loads Supported by Stiffened Flat Sheet Panels Under Edge Compression

Description: Note presenting testing of two series of stiffened flat sheet specimens tested under edge compression using various end conditions: round ends, flat ends, and continuous panels. The specimens consisted of aluminum-alloy flat sheet stiffened by three hat-shaped extruded aluminum-alloy stiffeners. The results indicated that the length of the specimen has an insignificant effect on the ultimate compressive load.
Date: June 1941
Creator: Holt, Marshall
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effects of Aerodynamic Heating on Ice Formations on Airplane Propellers

Description: Report presenting an investigation of the effect of aerodynamic heating on propeller-blade temperatures and its relation to propeller icing. Test results indicate that the outermost station at which ice formed on a propeller blade as determined by the blade temperature rise resulting from the aerodynamic heating at that point.
Date: March 1941
Creator: Rodert, Lewis A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Comparison of stress-strain curves obtained by single-thickness and pack methods

Description: Report presenting an apparatus for supporting a single thickness of sheet against buckling so that its compressive yield strength can be determined by the single-thickness method. The results of testing are compared with those from two other methods. This method results in substantial cost savings as compared to the pack method.
Date: August 1941
Creator: Paul, D. A.; Howell, F. M. & Grieshaber, H. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some comparative tests of plain and alclad 24S-T sheet

Description: Report presenting comparative data on the behavior of plain and alclad 24S-T sheet under several types of structural loading. Results indicated that as far as flexural stiffness and resistance to buckling are concerned, the effect of the soft protective coating on alclad shoot is equivalent to a reduction in thickness of about 7 percent. Results regarding the tensile and compressive properties of materials, bending tests on single thicknesses of sheet, column tests on single thicknesses of shee… more
Date: August 1941
Creator: Moore, R. L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-tunnel investigation of effect of yaw on lateral-stability characteristics 3: symmetrically tapered wing at various positions on circular fuselage with and without a vertical tail

Description: Report presenting testing of model combinations of an NACA 23012 tapered wing and a circular fuselage to determine the effect of longitudinal wing position on the change in lateral stability due to interference. Results regarding wing-fuselage interference and effect of wing-fuselage interference on vertical tail are provided.
Date: September 1941
Creator: Recant, Isidore G. & Wallace, Arthur R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Variation of Properties Throughout Cross Section of Two Extruded Shapes

Description: "Tensile and compressive properties were determined of specimens cut from the fins and the main bodies of two different extruded shapes of 24S-T aluminum alloy. The specimens from the fins as compared with those from the main body of the section showed: tensile strengths from 5000 to 10,000 pounds per square inch lower; tensile yield strengths and compressive yield strengths 4000 to 9000 pounds per square inch lower. The compressive yield strength values for any given location in the cross sect… more
Date: September 1941
Creator: Howell, F. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tandem Air Propellers - 2

Description: Report presenting testing of three-blade, adjustable-pitch counterrotating tandem model propellers adjusted to absorb equal power at maximum efficiency of the combination. The aerodynamic characteristics were determined for a variety of blade-angle settings and diameter spacings. At maximum efficiency, the tandem propellers absorb about double the power of the three-blade propellers and about 8 percent more power than six-blade propellers with the pitch of the forward propeller of the tandem co… more
Date: August 1941
Creator: Lesley, E. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Velocity gained and altitude lost in recoveries from inclined flight paths

Description: A series of charts is given showing the variation of the velocity gained and the altitude lost in dive pullouts with the initial indicated air speed and the dive angle. The effects of the maximum load factor, the drag parameter K, the initial altitude, and the type of recovery on the velocity gained and the altitude lost are also considered. The results were obtained from a step-by-step solution of the equations of motion in which mean values of the air density and the airplane drag coefficient… more
Date: October 1941
Creator: Pearson, H. A. & Garvin, J. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Method of Determining the Equilibrium Performance and the Stability of an Engine Equipped With an Exhaust Turbosupercharger

Description: "The performance of an exhaust turbine driving a supercharger is investigated by means of a sample calculation based on reasonable assumptions for the purpose of determining whether the assumed installation is stable with respect to changes in the mass of gas handled, boost pressure, etc. The arrangement was found to be stable throughout the entire range of operation. The method developed can be generally applied" (p. 1).
Date: November 1941
Creator: Rea, James Buchanan
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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