National Advisory Committee for Aeronautics (NACA) - 34 Matching Results

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Aircraft Power-Plant Instruments

Description: From Summary: "The report includes a description of the commonly used types and some others, the underlying principle utilized in the design, and some design data. The inherent errors of the instrument, the methods of making laboratory tests, descriptions of the test apparatus, and data in considerable detail in the performance of commonly used instruments are presented. Standard instruments and, in cases where it appears to be of interest, those used as secondary standards are described."
Date: May 31, 1933
Creator: Sontag, Harcourt & Brombacher, W. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Characteristics of Clark Y airfoils of small aspect ratios

Description: This report presents the results of a series of wind tunnel tests showing the force, moment, and autorotational characteristics of Clark Y airfoils having aspect ratios varying from 0.5 to 3. An airfoil of rectangular plan form was tested with rectangular tips, flared tips, and semicircular tips. Tests were also made on one airfoil of circular plan form and two airfoils of elliptical plan form. The tests revealed a marked delay of the stall and a decided increase in values of maximum lift coeff… more
Date: May 5, 1932
Creator: Zimmerman, C. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Combustion in a High-Speed Compression-Ignition Engine

Description: "An investigation conducted to determine the factors which control the combustion in a high-speed compression-ignition engine is presented. Indicator cards were taken with the Farnboro indicator and analyzed according to the tangent method devised by Schweitzer. The analysis show that in a quiescent combustion chamber increasing the time lag of auto-ignition increases the maximum rate of combustion. Increasing the maximum rate of combustion increases the tendency for detonation to occur" (p. 63… more
Date: May 21, 1931
Creator: Rothrock, A. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Computation of the two-dimensional flow in a laminar boundary layer

Description: A comparison is made of the boundary-layer flow computed by the approximate method developed by K. Pohlhausen with the exact solutions which have been published for several special cases. A modification of Pohlhausen's method has been developed which extends the range of application at the expense of some decrease in the accuracy of the approximations.
Date: May 1934
Creator: Dryden, Hugh L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A description and test results of a spark-ignition and a compression-ignition 2-stroke-cycle engine

Description: This report presents performance results of air cooled and water-cooled engines. The results obtained were sufficiently promising to warrant further investigation with fuel injection and spark ignition, with the same arrangement of inlet ports and exhaust valves at the bottom of the cylinder and the exhaust gases discharged through two poppet valves in the cylinder head. The displacement of the engine was 118 cubic inches. Optimum performance was obtained with the inlet air directed into the cy… more
Date: May 14, 1934
Creator: Spanogle, J. A. & Whitney, E. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of boundary-layer transition on three symmetrical airfoils in the NACA full-scale wind tunnel

Description: For the purpose of studying the transition from laminar to turbulent flow, boundary-layer measurements were made in the NACA full-scale wind tunnel on three symmetrical airfoils of NACA 0009, 0012, and 0018 sections. The effects of variations in lift coefficient, Reynolds number, and airfoil thickness on transition were investigated. Air speed in the boundary layer was measured by total-head tubes and by hot wires; a comparison of transition as indicated by the two techniques was obtained. The … more
Date: May 26, 1938
Creator: Silverstein, Abe & Becker, John V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Dynamic and flight tests on rubber-cord and oleo-rubber-disk landing gears for an F6C-4 airplane

Description: The investigation described in this report was conducted for the purpose of comparing an oleo-rubber-disk and a rubber-cord landing gear, built for use on an F6C-4 airplane. The investigation consisted of drop tests under various loading conditions and flight tests on an F6C-4 airplane. In the drop tests the total work done on each gear and the work done on each of the shock-absorbing units were determined. For both drop tests and flight tests the maximum loads and accelerations were determined… more
Date: May 20, 1930
Creator: Peck, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of area aspect ratio on the yawing moments of rudders at large angles of pitch on three fuselages

Description: This reports presents the results of measurements made of yawing moments produced by rudder displacement for seven rudders mounted on each of three fuselages at angles of pitch of 0 degree, 8 degrees, 12 degrees, 20 degrees, 30 degrees and 40 degrees. The dimensions of the rudders were selected to cover the range of areas and aspect ratios commonly used, while the ratios of rudder area to fin area and of rudder chord to fin chord were kept approximately constant. An important result of the meas… more
Date: May 16, 1932
Creator: Dryden, Hugh L. & Monish, B. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Compressibility on Eight Full-Scale Propellers Operating in the Take-Off and Climbing Range

Description: "Tests were made of eight full-scale propellers of different shape at various tip speeds up to about 1,000 feet per second. The range of blade-angle settings investigated was from 10 degrees to 30 degrees at the 0.75 radius. The results indicate that a loss in propulsive efficiency occurred at tip speeds from 0.5 to 0.7 the velocity of sound for the take-off and climbing conditions" (p. 517).
Date: May 18, 1938
Creator: Biermann, David & Hartman, Edwin P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of increased carburetor pressure on engine performance at several compression ratios

Description: The object of this investigation was to determine the effect of increasing the carburetor pressures from 30 to 40 inches of mercury, at compression ratios from 3.5 to 7.5, on the power, on the maximum cylinder pressures, on the fuel consumption, and on the other performance characteristics of an engine. A roots-type aircraft-engine supercharger was used to maintain the desired carburetor pressure.
Date: May 29, 1931
Creator: Schey, Oscar W. & Rollin, Vern G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of orifice length-diameter ratio on fuel sprays for compression-ignition engines

Description: "Experimental results on the effect of the length-diameter ratio of the orifice on the spray characteristics, together with a brief analysis of the factors affecting these characteristics, are presented in this report. The length-diameter ratios tested ranged from 0.5 to 10; the orifice diameters from 0.008 to 0.040 inch; and the injection pressures from 2,000 to 8,000 pounds per square inch. The density of the air into which the fuel was discharged was varied from 0.38 to 1.35 pounds per cubic… more
Date: May 27, 1931
Creator: Gelalles, A. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Verification of the Theory of Wind-Tunnel Boundary Interference

Description: "The results of an experimental investigation on the boundary-correction factor are presented in this report. The values of the boundary-correction factor from the theory, which at the present time is virtually completed, are given in the report for all conventional types of tunnels. With the isolation of certain disturbing effects, the experimental boundary-correction factor was found to be in satisfactory agreement with the theoretically predicted values, thus verifying the soundness and suff… more
Date: May 18, 1933
Creator: Theodorsen, Theodore & Silverstein, Abe
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Flame Movement and Pressure Development in an Engine Cylinder

Description: "This investigation describes a visual method for making stroboscopic observations, through a large number of small windows, of the spread of flame throughout the combustion chamber of a gasoline engine. Data, secured by this method on a small engine burning gaseous fuels, are given to show the effects of mixture ratio, spark advance, engine speed, charge density, degree of dilution, compression ratio, and fuel composition on flame movement in the cylinder. Partial indicator diagrams showing pr… more
Date: May 1, 1931
Creator: Marvin, Charles F., Jr. & Best, Robert D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Flight Investigation of the Lateral Control Characteristics of Short Wide Ailerons and Various Spoilers With Different Amounts of Wing Dihedral

Description: This report presents the results of flight tests made to determine the lateral control characteristics of short wide ailerons and spoilers, as a consequence of the promise shown in wind-tunnel tests by these devices as means of obtaining lateral control, particularly at angles of attack above the stall. Several forms of spoilers, front-hinge, rear-hinge, plain retractable, and saw-tooth retractable were tested alone and in combination with the ailerons. The tests were made with several differen… more
Date: May 19, 1934
Creator: Weick, Fred E.; Soulé, Hartley A. & Gough, Melvin N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Force measurements on a 1/40-scale model of the U. S. Airship "Akron"

Description: This report describes a series of tests made on a 1/40-scale model of the U. S. Airship "Akron" (ZRS-4) for the purpose of determining the drag, lift, and pitching moments of the bare hull and of the hull equipped with two different sets of fins. Measurements were also made of the elevator forces and hinge moments.
Date: May 6, 1932
Creator: Freeman, Hugh B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Fuel vaporization and its effect on combustion in a high-speed compression-ignition engine

Description: "The tests discussed in this report were conducted to determine whether or not there is appreciable vaporization of the fuel injected into a high-speed compression-ignition engine during the time available for injection and combustion. The effects of injection advance angle and fuel boiling temperature were investigated. The results show that an appreciable amount of the fuel is vaporized during injection even though the temperature and pressure conditions in the engine are not sufficient to ca… more
Date: May 4, 1932
Creator: Rothrock, A. M. & Waldron, C. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Full-scale tests of NACA cowlings

Description: A comprehensive investigation has been carried on with full-scale models in the NACA 20-foot wind tunnel, the general purpose of which is to furnish information in regard to the physical functioning of the composite propeller-nacelle unit under all conditions of take-off, taxiing, and normal flight. This report deals exclusively with the cowling characteristics under condition of normal flight and includes the results of tests of numerous combinations of more than a dozen nose cowlings, about a… more
Date: May 18, 1936
Creator: Theodorsen, Theodore; Brevoort, M. J. & Stickle, George W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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General Theory of Aerodynamic Instability and the Mechanism of Flutter

Description: "The aerodynamic forces on an oscillating airfoil or airfoil-aileron combination of three independent degrees of freedom were determined. The problem resolves itself into the solution of certain definite integrals, which were identified as Bessel functions of the first and second kind, and of zero and first order. The theory, based on potential flow and the Kutta condition, is fundamentally equivalent to the conventional wing section theory relating to the steady case" (p. 291).
Date: May 2, 1934
Creator: Theodorsen, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Full-Scale Split Trailing-Edge Wing Flaps With Various Chords and Hinge Locations

Description: This report gives the results of an investigation conducted in the NACA full-scale wind tunnel on a small parasol monoplane equipped with three different split trailing-edge wing flaps. The object of the investigation was to determine and correlate data on the characteristics of the airplane and flaps as affected by variation in flap chord, flap deflection, and flap location along the wing chord. The results give the lift, the drag, and the pitching moment characteristics of the airplane, and t… more
Date: May 10, 1935
Creator: Wallace, Rudolf
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An investigation of the drag of windshields in the 8-foot high-speed wind tunnel

Description: Report presents the results of tests made to determine the drag of closed-cockpit and transport-type windshields. The tests were made at speeds corresponding to a Mach number range of approximately 0.25 to 0.58 in the NACA 8-foot high-speed wind tunnel. This speed range corresponds to a test Reynolds number range of 2,510,000 to 4,830,000 based on the mean aerodynamic chord of the full-span model (17.29 in.). The shapes of the windshield proper, the hood, and the tail fairing were systematicall… more
Date: May 22, 1939
Creator: Robinson, Russell G. & Delano, James B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Lift and drag characteristics and gliding performance of an autogiro as determined in flight

Description: From Summary: "This report presents the results of flight test of the Pitcairn "PCA-2" autogiro. Lift and drag coefficients with the propeller stopped have been determined over approximately a 90 degree range of angles of attack. Based on the sum of fixed-wing and swept-disk areas, the maximum lift coefficient is 0.895, the minimum drag coefficient with propeller stopped is 0.015, and the maximum l/d with propeller stopped is 4.8. Lift coefficients were found also with the propeller delivering … more
Date: May 2, 1932
Creator: Wheatley, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Maneuverability investigation of the F6C-3 airplane with special flight instruments

Description: "This investigation was made for the purpose of obtaining information on the maneuverability of the F6C-3 airplane. It is the first of a series of similar investigations to be conducted on a number of military airplanes for the purpose of comparing the abilities of these airplanes to maneuver, and also to establish a fund of quantitative data which may be used in formulating standards of comparison for rating the maneuverability of any airplane. A large part of this initial investigation was ne… more
Date: May 23, 1930
Creator: Dearborn, C. H. & Kirschbaum, H. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Negative Thrust and Torque Characteristics of an Adjustable-Pitch Metal Propeller

Description: This report presents the results of a series of negative thrust and torque measurements made with a 4 foot diameter model of a conventional aluminum-alloy propeller. The tests were made in the 20-foot propeller-research tunnel of the National Advisory Committee for Aeronautics. The results show that the negative thrust is considerably affected by the shape and size of the body behind the propeller, that the maximum negative thrust increases with decrease in blade-angle setting, and that the dra… more
Date: May 23, 1933
Creator: Hartman, Edwin P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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