National Advisory Committee for Aeronautics (NACA) - 146 Matching Results

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The Effect of Surface Irregularities on Wing Drag 1 - Rivets and Spot Welds

Description: "Tests have been conducted in the NACA 8-foot high-speed wind tunnel to determine the effect of exposed rivet heads and spot welds on wing drag. Most of the tests were made with an airfoil of 5-foot chord. The air speed was varied from 80 to 500 miles per hour and the lift coefficient from 0 to 0.30" (p. 1).
Date: February 1938
Creator: Hood, Manley J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Surface Irregularities on Wing Drag 2 - Lap Joints

Description: Tests have been made in the NACA 8-foot high-speed wind tunnel of the drag caused by four types of lap joint. The tests were made on an airfoil of NACA 23012 section and 5-foot chord and covered in a range of speeds from 80 to 500 miles per hour and lift coefficients from 0 to 0.30. The increases in profile drag caused by representative arrangements of laps varied from 4 to 9%. When there were protruding rivet heads on the surface, the addition of laps increased the drag only slightly. Laps on … more
Date: February 1938
Creator: Hood, Manley J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Surface Irregularities on Wing Drag 3 - Roughness

Description: "Tests have been made in the N.A.C.A. 8-foot high-speed wind tunnel of the drag caused by roughness on the surface of an airfoil of N.A.C.A. 23012 section and 5-foot chord. The tests were made at speeds from 80 to 500 miles per hour at lift coefficients from 0 to 0.30. For conditions corresponding to high-speed flight, the increase in the drag was 30 percent of the profile drag of the smooth airfoil for the roughness produced by spray painting and 63 percent for the roughness produced. by 0.003… more
Date: February 1938
Creator: Hood, Manley J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Surface Irregularities on Wing Drag 4 - Manufacturing Irregularities

Description: "Tests were made in the NACA 8-foot high speed wind tunnel of a metal-covered, riveted, 'service' wing of average workmanship to determine the aerodynamic effects of the manufacturing irregularities incident to shop fabrication. The wing was of 5-foot chord and of NACA 23012 section and was tested in the low-lift range at speeds from 90 to 450 miles per hour corresponding to Reynolds numbers from 4,000,000 to 18,000,000. At a cruising condition the drag of the service wing was 46% higher than t… more
Date: February 1938
Creator: Robinson, Russell G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effective Width of Curved Sheet After Buckling

Description: This report describes experiments made for the purpose of ascertaining the effective width of circularly curved sheet under pure flexural stress. A relation for the effective width of curved sheets is established. Experiments were made with circular cylinders compressed in longitudinal direction. The sheets were rigidly built in at the sides parallel to the axis of the cylinder.
Date: November 1938
Creator: Wenzek, W. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effects of partial-span plain flaps on the aerodynamic characteristics of a rectangular and a tapered Clark Y wing

Description: An investigation was made to determine the aerodynamic characteristics of tapered and rectangular wings with partial-span plain flaps. Two Clark Y airfoils equipped with center section and with tip-section flaps were tested. The results showed that the aerodynamic characteristics of partial-span plain flaps were, in general, similar to those of split flaps of the same span, but that the lift and the drag were less for the wing with plain flaps than for the wing with split flaps of comparable si… more
Date: September 1938
Creator: House, R. O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effects of Simulated Ice Formation on the Aerodynamic Characteristics of an Airfoil

Description: Report presenting an investigation of the size and distribution of ice particles on the wings of aircraft and how they affect the aerodynamic characteristics. A simulated ice formation was generated from survey information received from aircraft pilots and was tested to determine the impact on the lift characteristics.
Date: May 1938
Creator: Gulick, Beverly G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Engine performance and knock rating of fuels for high-output aircraft engines

Description: From Summary: "Data are presented to show the effects of inlet-air pressure, inlet-air temperature, and compression ratio on the maximum permissible performance obtained on a single-cylinder test engine with aircraft-engine fuels varying from a fuel of 87 octane number to one 100 octane number plus 1 ml of tetraethyl lead per gallon. The data were obtained on a 5-inch by 5.75-inch liquid-cooled engine operating at 2,500 r.p.m. The compression ratio was varied from 6.50 to 8.75. The inlet-air te… more
Date: April 1938
Creator: Rothrock, A. M. & Biermann, Arnold E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Engines and Propellers for Powered Gliders and Light Airplanes

Description: The object of the present paper is to consider the interaction of engine, propeller, and airplane for the low-power range. The discussion is presented in a form so as to provide the engine builder with a basis in his selection in the type of engine required, a suitable selection being possible only in connection with considerations on the best possible propeller.
Date: March 1938
Creator: Gropp, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The estimation of the rate of change of yawing moment with sideslip

Description: "Wind-tunnel data are presented on the rate of change of yawing moment with sideslip for tests of 9 complete airplane models, 20 fuselage shapes, and 3 wing models with various combinations of dihedral, sweepback, and twist. The data were collected during a survey of existing information, which was made to find a reliable method of computing the yawing moment due to sideslip. Important errors common to methods of computation used at present appear to be due to large interference effects, the in… more
Date: February 1938
Creator: Imlay, Frederick H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Study of Ignition by Hot Spot in Internal Combustion Engines

Description: "In order to carry out the contemplated study, it was first necessary to provide hot spots in the combustion chamber, which could be measured and whose temperature could be changed. It seemed difficult to realize both conditions working solely on the temperature of the cooling water in a way so as to produce hot spots on the cylinder wall capable of provoking autoignition. Moreover, in the majority of practical cases, autoignition is produced by the spark plug, one of the least cooled parts in … more
Date: August 1938
Creator: Serruys, Max
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fatigue Testing of Wing Beam by the Resonance Method

Description: "Preliminary fatigue tests on two aluminum-alloy wing-beam specimens subjected to reversed axial loading are described. The motion used consists in incorporating one or two reciprocating motors in a resonance system of which the specimen is the spring element. A description is given of the reciprocating motors, and of the method of assembling and adjusting the vibrating system" (p. 1).
Date: August 1938
Creator: Bleakney, William M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flight and wind-tunnel tests of an XBM-1 dive bomber

Description: From Summary: "Results are given of pressure-distribution measurements made in flight over the right wing cellule and the right half of the horizontal tail surfaces of a dive-bombing biplane. Simultaneous measurements were also taken of the air speed, control-surface positions, control forces, and normal accelerations during various abrupt maneuvers in vertical plane. These maneuvers consisted of push-downs and pull-ups from level flight, dives and dive pull-ups from inverted flight. Besides th… more
Date: April 1938
Creator: Donely, Philip & Pearson, Henry A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A flight investigation of the reduction of aileron operating force by means of fixed tabs and differential linkage, with notes on linkage design

Description: Flight tests were made to demonstrate the particularity of employing fixed tabs in conjunction with a suitably designed differential linkage to reduce the force required to operate ailerons. The tests showed the system to be practicable with tabs of the inset type. The relative ineffectiveness of attached tabs for changing the aileron floating angle rendered them unsuitable. Experience gained in the investigation has indicated that the use of the system is limited to maximum deflections of one … more
Date: June 1938
Creator: Soulé, H. A. & Hootman, James A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flow in Smooth Straight Pipes at Velocities Above and Below Sound Velocity

Description: "To investigate the laws of flow of compressible fluids in pipes, tests were carried out with air flowing at velocities below and above that of sound in straight smooth pipes. Air was chosen as the flow medium. In order that the effect of compressibility may be brought out most effectively, the velocity should lie between 100 and 500 m/s (200 and 1,000 mph); that is, be of the order of magnitude of the velocity of sound in air. The behavior of the compression shock in a smooth cylindrical pipe … more
Date: January 1938
Creator: Frössel, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flow observations with tufts and lampblack of the stalling of four typical airfoil sections in the NACA variable-density tunnel

Description: From Summary: "A preliminary investigation of the stalling processes of four typical airfoil sections was made over the critical range of the Reynolds Number. Motion pictures were taken of the movements of small silk tufts on the airfoil surface as the angle of attack increased through a range of angles including the stall. The boundary-layer flow also at certain angles of attack was indicated by the patterns formed by a suspension of lampblack in oil brushed onto the airfoil surface. These obs… more
Date: October 1938
Creator: Abbott, Ira H. & Sherman, Albert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Focke helicopter

Description: This report presents some of the problems concerning tests of helicopters, such as forced landings, controllability and stability, general safety, piloting maneuvers, performance, servicing, and the production of lift of a propeller. Test flights are described including a 67.67 mph flight by Hanna Reitsch.
Date: April 1938
Creator: Focke, H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-spinning wind-tunnel tests of a low-wing monoplane with systematic changes in wings and tails 3: mass distributed along the wings

Description: Report presenting an investigation of 24 wing-tail combinations with the weight moved from the center of gravity toward the wing tips so that the distribution of mass along the wings was increased. Results regarding the effects of wings, effects of tail arrangement, effects of control setting, relationships between spin characteristics, and comparison with results for basic loading are provided.
Date: September 1938
Creator: Seidman, Oscar & Neihouse, A. I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fuel Consumption of a Carburetor Engine at Various Speeds and Torques

Description: "An investigation was conducted to obtain fuel-consumption curves for a single-cylinder engine with a Wright 1820-G and Pratt & Whitney 1340-H cylinder at varying speeds, manifold pressures, and air-fuel ratios. The 1340- H cylinder was tested at speeds from 1,200 to 2,400 r.p.m. and at manifold pressures from 21 to 38 inches of mercury absolute. Less than extensive tests were made of the 1820-G cylinder. The results of the tests showed that the minimum brake fuel consumption was obtained when … more
Date: June 1938
Creator: Schey, Oscar W. & Clark, J. Denny
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Full-Scale Wind-Tunnel Investigation of Wing Cooling Ducts, Special Report

Description: "The systematic investigation of wing cooling ducts at the NACA laboratory has been continued with tests in the full-scale wind tunnel on ducts of finite span. These results extend the previous investigation on section characteristics of ducts to higher Reynolds numbers and indicate the losses due to the duct ends. The data include comparisons between ducts completely within the ring and the conventional underslung ducts" (p. 1).
Date: October 1938
Creator: Nickle, F. R. & Freeman, Arthur B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A general tank test of a model of the hull of the Pem-1 flying boat including a special working chart for the determination of hull performance

Description: The results of a general tank test of a 1/6 full-size model of the hull of the P3M-1 flying boat (N.A.C.A. model 18) are given in non-dimensional form. In addition to the usual curves, the results are presented in a new form that makes it possible to apply them more conveniently than in the forms previously used. The resistance was compared with that of N.A.C.A. models 11-C and 26(Sikorsky S-40) and was found to be generally less than the resistance of either.
Date: December 1938
Creator: Dawson, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Generalized Analysis of Experimental Observations in Problems of Elastic Stability

Description: "A generalized method of analyzing experimental observations in problems of elastic stability is presented in which the initial readings of load and deflection may be taken at any load less the critical load. The analysis is an extension of a method published by Southwell in 1932, in which it was assumed that the initial readings are taken at zero load" (p. 1).
Date: July 1938
Creator: Lundquist, Eugene E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Gyroscopic Instruments for Instrument Flying

Description: The gyroscopic instruments commonly used in instrument flying in the United States are the turn indicator, the directional gyro, the gyromagnetic compass, the gyroscopic horizon, and the automatic pilot. These instruments are described. Performance data and the method of testing in the laboratory are given for the turn indicator, the directional gyro, and the gyroscopic horizon. Apparatus for driving the instruments is discussed.
Date: September 1938
Creator: Brombacher, W. G. & Trent, W. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Heat-Stressed Structural Components in Combustion-Engine Design

Description: "Heated structural parts alter their shape. Anything which hinders free heat expansion will give rise to heat stresses. Design rules are thus obtained for the heated walls themselves as well as for the adjoining parts. An important guiding principle is that of designing the heat-conducting walls as thin as possible" (p. 1).
Date: September 1938
Creator: Kraemer, Otto
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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