National Advisory Committee for Aeronautics (NACA) - 417 Matching Results

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Effect of Combustion-Chamber Shape on the Performance of a Prechamber Compression-Ignition Engine

Description: "The effect on engine performance of variations in the shape of the prechamber, the shape and direction of the connecting passage, the chamber volume using a tangential passage, the injection system, and the direction of the fuel spray in the chamber was investigated using a 5 by 7 inch single-cylinder compression-ignition engine. The results show that the performance of this engine can be considerably improved by selecting the best combination of variables and incorporating them in a single de… more
Date: December 1934
Creator: Moore, C. S. & Collins, J. H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of connecting-passage diameter on the performance of a compression-ignition engine with a precombustion chamber

Description: Results of motoring tests are presented showing the effect of passage diameter on chamber and cylinder compression pressures, maximum pressure differences, and f.m.e.p. over a speed range from 300 to 1,750 r.p.m. Results of engine performance tests are presented which show the effect of passage diameter on m.e.p., explosion pressures, specific fuel consumption, and rates of pressure rise for a range of engine speeds from 500 to 1,500 r.p.m. The cylinder compression pressure, the maximum pressur… more
Date: November 1932
Creator: Moore, C. S. & Collins, J. H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Curvature on the Transition From Laminar to Turbulent Boundary Layer

Description: Note presenting a discrepancy between the predicted and actual point of transition from laminar to turbulent boundary layer that had been found. This effect may be due to the comparatively small radius of curvature of the upper surface of the wing.
Date: September 1937
Creator: Clauser, Milton & Clauser, Francis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Curvature on the Transition From Laminar to Turbulent Boundary Layer

Description: "In the flow over the upper surface of a wing, a discrepancy between the predicted and actual point of transition from laminar to turbulent boundary layer was found. This effect may be due to the comparatively small radius of curvature of the upper surface of the wing. Tests were undertaken to investigate this effect. As far as the authors know, the present investigation is the first to show that curvature has a pronounced effect on the transition of the boundary layer from the laminar to the t… more
Date: September 1937
Creator: Clauser, Milton & Clauser, Francis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Depth of Step on the Water Performance of a Flying-Boat Hull Model N.A.C.A. Model 11-C

Description: "NACA model 11-C was tested with four different depths of step to obtain information as to the effect of the depth of step on the water performance. The depths of step were selected to cover the practicable range of depths and in each case the included angle between the forebody and afterbody keels was kept the same 6-1/2 degrees. Small depths of step were found to give lower resistance at speeds below and at the hump speed of the model and greater depths of step lower resistance at high speeds… more
Date: July 1935
Creator: Bell, Joe W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of engine operating conditions on the vaporization of safety fuels

Description: "Tests were conducted with the N.A.C.A. combustion apparatus to determine the effect of compression ratio and engine temperature on the vaporization of a hydrogenated "safety fuel" during the compression stroke under conditions similar to those in a spark-ignition engine. The effects of fuel boiling temperature on vaporization using gasoline, safety fuel, and Diesel fuel oil was also investigated. The results show that increasing the compression ratio has little effect on the rate of fuel vapor… more
Date: August 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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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
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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Effect of Length of Handley Page Tip Slots on the Lateral-Stability Factor, Damping in Roll

Description: "Tests have been made in the NACA 7 by 10 foot wind tunnel on a Clark Y wing model equipped with various lengths of Handley Page slots extending inward from the wing tips. The slot lengths tested ranged from 20 to 100 per cent of the semi span. The effect of slot lengths on damping in roll was determined by means of both free-autorotation and forced-rotation test. In addition, the maximum lift coefficient was found with each slot length. The optimum length of slot for satisfactory damping in ro… more
Date: July 1932
Creator: Weick, Fred E. & Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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Effect of Orifice Length-Diameter Ratio on Spray Characteristics

Description: "The effect of variations of orifice length to diameter ratio on spray characteristics was determined for a 0.014-inch and a 0.040-inch orifice for ratio of 0.5 to 4.0. The nozzles containing the orifices were mounted in an injection valve and tested with a plan stem and with a helically grooved stem. The injection pressure was varied from 4000 to 8000 pounds per square inch. The air density into which the fuel was sprayed was varied from the density obtained with a pressure of 60 pounds per sq… more
Date: October 1930
Creator: Gelalles, A. 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 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
Partner: UNT Libraries Government Documents Department
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The Effect of Partial-Span Split Flaps on the Aerodynamic Characteristics of a Clark Y Wing

Description: "Aerodynamic force tests were made in the N.A.C.A. 7 by 10 foot wind tunnel on a model Clark Y wing with a 20 percent chord split flap deflected 60 degrees downward. The tests were made to determine the effect of partial-span split flaps, located at various positions along the wing span on the aerodynamic characteristics of the wing-and-flap combination. The different lengths and locations of the flaps were obtained by cutting off portions of a full-span flap, first from the tips and then from … more
Date: September 1933
Creator: Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Propellers and Nacelles on the Landing Speeds of Tractor Monoplanes

Description: "This paper reports wind-tunnel tests giving the lift coefficients of large-scale wing-nacelle combinations both with and without the propeller. The tests were made to show the effect of nacelles, and idling and stopped propellers on the landing speeds of tractor monoplanes. Four types of nacelles with various cowlings were used in numerous positions with respect to both a Clark Y and a thick airfoil. The effect of both the idling and stopped propeller on lift, and consequently on landing speed… more
Date: May 1932
Creator: Windler, Ray
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Retractable-Spoiler Location on Rolling- and Yawing-Moment Coefficients

Description: "In this report are presented the results of wind-tunnel tests of retractable spoilers on the upper surface of a Clark Y wing, which have been made as part of an investigation of lateral control devices being conducted by the National Advisory Committee for Aeronautics. Spoilers with chords up to 15.0 percent of the wing chord were tested in several locations on a plain rectangular wing and in two locations on the same wing equipped with a 20.0 percent chord split flap down 60 degrees. Charts a… more
Date: July 1934
Creator: Shortal, J. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Rivet Heads on the Characteristics of a 6 by 36 Foot Clark Y Metal Airfoil

Description: "An investigation was conducted in the N.A.C.A. full-scale wind tunnel to determine the effects of exposed rivet heads on the aerodynamic characteristics of a metal-covered 6 by 36 foot Clark Y airfoil. Lead punching simulating 1/8 inch rivet heads were attached in full-span rows at a pitch of 1 inch at various chord positions. Tests were made at velocities varying from 40 to 120 miles per hour to investigate the scale effect" (p. 1).
Date: May 1933
Creator: Dearborn, Clinton H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Several Factors on the Cooling of a Radial Engine in Flight

Description: "Flight tests of a Grumman Scout (XSF-2) airplane fitted with a Pratt & Whitney 1535 supercharged engine were conducted to determine the effect of engine power, mass flow of the cooling air, and atmospheric temperature on cylinder temperature. The tests indicated that the difference in temperature between the cylinder wall and the cooling air varied as the 0.38 power of the brake horsepower for a constant mass flow of cooling air, cooling-air temperature, engine speed, and brake fuel consumptio… more
Date: November 1936
Creator: Schey, Oscar W. & Pinkel, Benjamin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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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
Partner: UNT Libraries Government Documents Department
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Effect of spark-timing regularity on the knock of engine performance

Description: Tests on a high-speed single-cylinder engine are described. The regularity of the spark timing was varied by driving the timer from different engine shafts. A simple and reasonably accurate method of determining the spark timing is described. The results show that irregular spark timing may cause large errors in tests of the knocking properties of fuels. For the engine tested, it was found that a change of one crankshaft degree in spark restart was equivalent to an 0.85 inch Hg change in allowa… more
Date: May 1938
Creator: Biermann, Arnold E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Split Trailing-Edge Wing Flaps on the Aerodynamic Characteristics of a Parasol Monoplane

Description: "This paper presents the results of tests conducted in the N.A.C.A. full-scale wind tunnel on a Fairchild F-22 airplane equipped with a special wing having split trailing-edge flaps. The flaps extended over the outer 90 percent of the wing span, and were of the fixed-hinge type having a width equal to 20 percent of the wing chord. The results show that with a flap setting of 59 degrees the maximum lift of the wing was increased 42 percent, and that the flaps increased the range of available gli… more
Date: November 1933
Creator: Wallace, Rudolf N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of spray strips on a model of the P3M-1 flying boat hull

Description: This note presents the results of a series of tests made in the N.A.C.A. tank on a one-sixth full-size model of the hull and side floats of the Navy P3M-1 flying boat for the purpose of finding a method of reducing the amount of spray thrown into the propellers of this craft when taking off and landing. The model was tested without spray strips and with five different spray-strip arrangements. The best arrangement was an improvement over the bare hull with no spray strips, but the improvement w… more
Date: December 1933
Creator: Dawson, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of stabilizer location upon pitching and yawing moments in spins as shown by tests with the spinning balance

Description: Tests were made with the spinning balance in a 5-foot wind tunnel to study the effect of stabilizer location upon the pitching and yawing moments given by the tail surfaces in spinning attitudes. The tests revealed that the horizontal surfaces, when in a normal location, seriously reduced the effectiveness of the fin and rudder, particularly at angles of attack of 50 degrees or more. The tests also revealed that a more forward or more rearward location gave no consistent or decided improvement;… more
Date: November 1933
Creator: Bamber, M. J. & Zimmerman, C. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of the Angle of Afterbody Keel on the Water Performance of a Flying-Boat Hull Model

Description: NACA model 11-C was tested according to the general method with the angle of afterbody keel set at five different angles from 2-1/2 degrees to 9 degrees, but without changing other features of the hull. The results of the tests are expressed in curves of test data and of non-dimensional coefficients. At the depth of step used in the tests, 3.3 percent beam, the smaller angles of afterbody keel give greater load-resistance ratios at the hump speed and smaller at high speed than the larger angles… more
Date: September 1935
Creator: Allison, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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