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Determination of Resistance and Trimming Moment of Planing Water Craft

Description: This report presents a new theory which makes it possible to interpret the resistance and the trimming moment for any loading of a planing aircraft when these values are given for one load. This application of the new theory forms the basis of the present paper. Derivations of various conversion formulas are given as well as numerous examples.
Date: May 1931
Creator: Schröder, P.
Item Type: Refine your search to only Report
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Development and Production History on the Salt Flat and Other Fault Fields of East Central Texas

Description: Report issued by the Bureau of Mines over the Salt Flat fields in East Central Texas. As stated in the introduction, "this report deals with the development and production history of the Salt Flat field and gives comparative data on five outstanding fault fields. Two of these fields are producing from limestone and three from sandstone reservoirs" (p. 2-3). This report includes tables, maps, photographs, and illustrations.
Date: March 1931
Creator: Hill, Harry Blackburn; Bauserman, E. V. H. & Carpenter, C. B.
Item Type: Refine your search to only Report
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The development, design and construction of gliders and sailplanes

Description: This report explains and details the history of glider design and construction through the impetus of the Rhon Sailplane contests. Some of the topics considered include: whether the longitudinal stability (dynamic and static) is sufficient in the tailless typo and a consideration that the structural weight of sweptback wings would be greater than that of a corresponding normal wing.
Date: September 1931
Creator: Lippisch, A.
Item Type: Refine your search to only Report
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Development of a Non-Autorotative Airplane Capable of Steep Landing

Description: In the following we develop a non-autorotating monoplane wing. The conditions imposed on such a wing, aside from its freedom from autorotation,with respect to its polars and its construction, are taken into account as far as possible. It is indicated that the autorotation characteristics of a wing are dependent upon the speed of air flow as well as on the angle of yaw. This report postulates the knowledge of the behavior of certain conventional wings of different chords and cambers with respect… more
Date: December 1931
Creator: Schmidt, Wilhelm
Item Type: Refine your search to only Report
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Development of an Impinging-Jet Fuel-Injection Valve Nozzle

Description: "During an investigation to determine the possibilities and limitations of a two-stroke-cycle engine and ignition, it was necessary to develop a fuel injection valve nozzle to produce a disk-shaped, well dispersed spray. Preliminary tests showed that two smooth jets impinging upon each other at an angle of 74 degrees gave a spray with the desired characteristics. Nozzles were built on this basis and, when used in fuel-injection valves, produced a spray that fulfilled the original requirements" … more
Date: April 1931
Creator: Spanogle, J. A. & Hemmeter, G. T.
Item Type: Refine your search to only Report
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Downwash Measurements Behind Wings With Detached Flow

Description: This investigation, which was made in the small wind tunnel having a diameter of 1.2 m (3.94 feet), embraced three wing models, behind which, at various angles of attack between 0 and 60 degrees, the static pressure and the total pressure along vertical lines (perpendicular to the direction of the undisturbed wind and to the wing span) were measured. The location of these vertical lines are indicated in Figure 1. Moreover, the wing polars were determined by the customary three-component measure… more
Date: August 1931
Creator: Petersohn, E.
Item Type: Refine your search to only Report
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The drag characteristics of several airships determined by deceleration tests

Description: This report presents the results of deceleration tests conducted for the purpose of determining the drag characteristics of six airships. The tests were made with airships of various shapes and sizes belonging to the Army, the Navy, and the Goodyear-Zeppelin Corporation. Drag coefficients for the following airships are shown: Army TC-6, TC-10, and TE-2; Navy Los Angeles and ZMC-2; Goodyear Puritan. The coefficients vary from about 0.045 for the small blunt airships to 0.023 for the relatively l… more
Date: March 2, 1931
Creator: Thompson, F. L. & Kirschbaum, H. W.
Item Type: Refine your search to only Report
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Drop and Flight Tests on NY-2 Landing Gears Including Measurements of Vertical Velocities at Landing

Description: This investigation was conducted to obtain quantitative information on the effectiveness of three landing gears for the NY-2 (consolidated training) airplane. The investigation consisted of static, drop, and flight tests on landing gears of the oleo-rubber-disk and the mercury rubber-chord types, and flight tests only on a landing gear of the conventional split-axle rubber-cord type. The results show that the oleo gear is the most effective of the three landing gears in minimizing impact forces… more
Date: August 7, 1931
Creator: Peck, W. C. & Beard, A. P.
Item Type: Refine your search to only Report
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Effect of High Air Velocities on the Distribution and Penetration of a Fuel Spray

Description: "By means of the NACA Spray Photography Equipment high speed moving pictures were taken of the formation and development of fuel sprays from an automatic injection valve. The sprays were injected normal to and counter to air at velocities from 0 to 800 feet per second. The air was at atmosphere temperature and pressure. The results show that high air velocities are an effective means of mixing the fuel spray with the air during injection" (p. 1).
Date: May 1931
Creator: Rothrock, A. M.
Item Type: Refine your search to only Report
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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
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The Effect of Injection-Valve Opening Pressure on Spray-Tip Penetration

Description: "The effect of various injection-valve opening pressures on the spray-tip penetration was determined for several injection pressure. A common-rail fuel injection system was used. For a given injection pressure a maximum rate of penetration was obtained with an injection-valve opening pressure equal to the injection pressure" (p. 1).
Date: July 1931
Creator: Rothrock, A. M. & Marsh, E. T.
Item Type: Refine your search to only Report
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Effect of Nose Shape on the Characteristics of Symmetrical Airfoils

Description: Tests of nine symmetrical airfoils, having different leading-edge radii, were made in the variable density wind tunnel. Three symmetrical NACA airfoils having maximum thickness-to-chord ratio of 0.06, 0.012, and 0.018 were used as basic (or normal) sections; and for each of these thicknesses one thinner and one blunter nose section were developed. Although the slope of the lift curve varies with thickness, these tests show that for any given thickness the slope is independent of nose radius.
Date: August 1931
Creator: Pinkerton, Robert M.
Item Type: Refine your search to only Report
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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
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Effect of Orifice Length-Diameter Ratio on the Coefficient of Discharge of Fuel-Injection Nozzles

Description: The variation of the coefficient of discharge with the length-diameter ratio of the orifice was determined for nozzles having single orifice 0.008 and 0.020 inch in diameter. Ratios from 0.5 to 10 were investigated at injection pressures from 500 to 5,000 pounds per square inch. The tests showed that, within the error of the observation, the coefficients were the same whether the nozzles were assembled at the end of a constant tube or in an automatic injection valve having a plain stem.
Date: March 1931
Creator: Gelalles, A. G. & Marsh, E. T.
Item Type: Refine your search to only Report
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The effect of slots and flaps on the lift and drag of the McDonnell Airplanes determined in flight

Description: This note contains the results of flight test conducted by the National Advisory Committee for Aeronautics on a low-wing monoplane equipped with leading-edge slots extending over the entire wing and flaps extending only to the ailerons, to find their effect on the lift and drag characteristics of the airplane. Curves are given showing the lift and drag characteristics of the airplane for the following conditions of the slots and flaps neutral; slots closed and flaps down; and slots open and fla… more
Date: November 1931
Creator: Soulé, Hartley A.
Item Type: Refine your search to only Report
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The effect of small angles of yaw and pitch on the characteristics of airplane propellers

Description: This report presents the results of wind tunnel tests to determine the effect on the characteristics of a propeller of inclining the propeller axis at small angles to the relative wind. Tests were made of a full-scale propeller and fuselage combination at four angles of yaw (0 degree, +5 degrees, +10 degrees, +15 degrees), and of a model propeller, nacelle, and wing combination of five angles of pitch (-5 degrees, 0 degree, +5 degrees, +10 degrees and +15 degrees). The results of the full-scale… more
Date: January 20, 1931
Creator: Freeman, Hugh B.
Item Type: Refine your search to only Report
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The effect of small variations in profile of airfoils

Description: This report deals with the effect of small variations in ordinates specified by different laboratories for the airfoil section. This study was made in connection with a more general investigation of the effect of small irregularities of the airfoil surface on the aerodynamic characteristics of an airfoil. These tests show that small changes in airfoil contours, resulting from variations in the specified ordinates, have a sufficiently large effect upon the airfoil characteristics to justify the … more
Date: January 1931
Creator: Ward, Kenneth E.
Item Type: Refine your search to only Report
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Effect of Stabilizing Forces on Turbulence

Description: The appearance of expressed discontinuity layers in the free atmosphere, where a warm air mass flows over a cold mass without perceptible intermingling forms the basis of the present report. In these experiments an air stream is to be blown between a water-cooled and a vapor-heated plate. According to what preceded it is anticipated that the exchange will be enhanced.
Date: June 1931
Creator: Prandtl, L.
Item Type: Refine your search to only Report
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The effect of valve timing upon the performance of a supercharged engine at altitude and an unsupercharged engine at sea level

Description: This investigation was conducted to determine the comparative effects of valve timing on the performance of an unsupercharged engine at sea level and a supercharged engine at altitude. The tests were conducted on the NACA universal test engine. The timing of the four valve events was varied over a wide range; the engine speeds were varied between 1,050 and 1,500 r.p.m.; the compression ratios were varied between 4.35:1 and 7.35:1. The conditions of exhaust pressure and carburetor pressure of a … more
Date: February 4, 1931
Creator: Schey, Oscar W. & Biermann, Arnold E.
Item Type: Refine your search to only Report
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Effect of Viscosity in Speed Measurements With Double-Throat Venturi Tubes

Description: In order to clarify the viscosity effect some experiments were made in the Gottigen low-pressure tunnel with the Bruhn double-throat Venturi tube. This type of tunnel makes it possible to vary the pressure and thereby the density within wide limits and consequently, to examine the viscosity effect. This, however, did not impair the results because pressure and temperature were determined at different periods.
Date: August 1931
Creator: Peters, H.
Item Type: Refine your search to only Report
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The effect on airplane performance of the factors that must be considered in applying low-drag cowling to radial engines

Description: From Summary: "This report presents the results of flight tests with three different airplanes using several types of low-drag cowling for radial air-cooled engines. The greater part of the tests were made with a Curtiss XF7Cc-1 (Sea Hawk) with a 410 horsepower. Wasp engine, using three fuselage nose shapes and six types of outer cowling. The six cowlings were: a narrow ring, a wide ring, a wide cowling similar in the original NACA cowling, a thick ring incorporating an exhaust collector, a sin… more
Date: November 25, 1931
Creator: McAvoy, William H.; Schey, Oscar W. & Young, Alfred W.
Item Type: Refine your search to only Report
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The effectiveness of a double-stem injection valve in controlling combustion in a compression-ignition engine

Description: An investigation was made to determine to what extent the rates of combustion in a compression-ignition engine can be controlled by varying the rates of fuel injection. The tests showed that the double-stem valve operated satisfactorily under all normal injection conditions; the rate of injection has a definite effect on the rate of combustion; the engine performance with the double-stem valve was inferior to that obtained with a single-stem valve; and the control of injection rates permitted b… more
Date: December 1931
Creator: Spanogle, J. A. & Whitney, E. G.
Item Type: Refine your search to only Report
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