Technical Report Archive & Image Library (TRAIL) - 43 Matching Results

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The Drag of Streamline Wires

Description: "Preliminary results are given of drag tests of streamline wires. Full-size wires were tested over a wide range of speeds in the N.A.C.A. high speed tunnel. The results are thus directly applicable to full-scale problems and include any compressibility effects encountered at the higher speeds. The results show how protuberances may be employed on conventional streamline wires to reduce the drag, and also show how the conventional wires compare with others having sections more like strut or symm… more
Date: December 1933
Creator: Jacobs, Eastman N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of aileron displacement on wing characteristics

Description: The effect of aileron displacement on wing characteristics has been investigated for the Clark Y and the U.S.A. 27 wing sections equipped with rectangular ailerons. The airfoils, rectangular in plan, and having a 10 inch chord and 60 inch span, were mounted on a model fuselage.
Date: February 1933
Creator: Heald, R. H.
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 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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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 on Engine Performance of Change in Jacket-Water Outlet Temperature

Description: Tests made on a Curtiss D-12 engine in the Altitude Laboratory at the Bureau of Standards show the following effects on engine performance of change in jacket-water outlet temperature: 1) Friction at all altitudes is a linear function of the jacket-water temperature, decreasing with increasing temperature. 2) The brake horsepower below an altitude of about 9,000 feet decreases, and at higher altitudes increases, with jacket-water temperature. 3) The brake specific fuel consumption tends to decr… more
Date: November 1933
Creator: Garlock, E. A. & Ellis, Greer
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effects of slots and flaps on lateral control of a low-wing monoplane as determined in flight

Description: This paper presents the results of flight tests made to determine the effect of slots and flaps on the lateral control of a low-wing monoplane. Maximum angular accelerations in roll and yaw produced by sudden application of the ailerons and maximum accelerations in yaw produced by sudden application of the rudder during gliding flight were recorded for the following wing arrangements: (a) no auxiliary device; (b) full-span slots; (c) plain flaps; (d) flaps and full-span slots; (e) wing-tip slot… more
Date: November 1933
Creator: Soulé, Hartley A. & Wetmore, J. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Engine performance with a hydrogenated safety fuel

Description: From Summary: "This report presents the results of an investigation to determine the engine performance obtained with a hydrogenated safety fuel developed to eliminate fire hazard. The tests were made on a single-cylinder universal test engine at compression ratios of 5.0, 5.5, and 6.0. Most of the tests were made with a fuel-injection system, although one set of runs was made with a carburetor when using gasoline to establish comparative performance. The tests show that the b.m.e.p. obtained w… more
Date: July 1933
Creator: Schey, Oscar W. & Young, Alfred W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experiments With a Counter-Propeller

Description: This note describes tests made at Stanford University on a four-blade fixed counter-propeller in combination with a two-blade rotating propeller. It is shown that the efficiency of the normal form, well-designed air propeller can be increased about two percent over the full working range by the addition of fixed counter-propeller blades.
Date: March 1933
Creator: Lesley, E. P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Formulas for the Stress Analysis of Circular Rings in a Monocoque Fuselage

Description: "The formulas given in this report provide a simplified method for the stress-analysis of fuselage bulkheads that are approximately circular rings of uniform cross section. Complicated load systems acting on a ring can usually be resolved into simplified load systems; and formulas for moment, axial force, and shear for such simplified load systems are given in this report. Illustrative examples showing the use of this method in practical stress-analysis work are also included" (p. 1).
Date: June 1933
Creator: Miller, Roy A. & Wood, Karl D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Full-Scale Wind-Tunnel Research on Tail Buffeting and Wing-Fuselage Interference of a Low-Wing Monoplane

Description: Some preliminary results of full scale wind tunnel testing to determine the best means of reducing the tail buffeting and wing-fuselage interference of a low-wing monoplane are given. Data indicating the effects of an engine cowling, fillets, auxiliary airfoils of short span, reflexes trailing edge, propeller slipstream, and various combinations of these features are included. The best all-round results were obtained by the use of fillets together with the National Advisory Committee for Aerona… more
Date: May 1933
Creator: Hood, Manley J. & White, James A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The importance of auto-ignition lag in knocking

Description: Report presenting an examination of the phenomenon of knocking, which is often accompanied by an apparently simultaneous reaction of the last part of the charge to burn. Several hypotheses regarding the burning of fuel and an exploration of current literature regarding the phenomena are provided.
Date: March 1933
Creator: Taylor, E. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Jet Propulsion with Special Reference to Thrust Augmenters

Description: An investigation of the possibility of using thrust augmented jets as prime movers was carried out. The augmentation was to be effected by allowing the jet to mix with the surrounding air in the presence of bodies which deflect the air set in motion by the jet. Six augmentation schemes were tested experimentally with compressed air at room temperature at jet speeds up to 1240 feet per second.
Date: January 1933
Creator: Schubauer, G. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Mercerization of Cotton for Strength With Special Reference to Aircraft Cloth

Description: The object of the present investigation was to determine the conditions for mercerizing cotton yarn to obtain the maximum strength for a given weight. Apparatus for controlling the variables was built and yarns were mercerized with it under systematically varied conditions of tension, time, temperature, and concentration of caustic soda. The strongest conclusion to be drawn from this work is that the strongest mercerized yarn of a given count from a given quality of cotton is obtained under cer… more
Date: February 1933
Creator: Wilkie, J. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The N.A.C.A. Combustion Chamber Gas-Sampling Valve and Some Preliminary Test Results

Description: "A gas sampling valve of the inertia-operated type was designed for procuring samples of the gases in the combustion chamber of internal combustion engines at identical points in successive cycles so that the analysis of the gas samples thus procured may aid in the study of the process of combustion. The operation of the valve is described. The valve was used to investigate the CO2 content of gases taken from the quiescent combustion chamber of a high speed compression-ignition engine when oper… more
Date: March 1933
Creator: Spanogle, J. A. & Buckley, E. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Reduction in Drag of a Forward-Sloping Windshield

Description: "This paper gives results of a short investigation of the drag of a forward-sloping closed-cabin windshield. The drag of the windshield in both the original and a final modified form was determined from tests in the variable-density wind tunnel. The final form of the windshield was arrived at by modifying the original as the result of flow observations in the N.A.C.A. smoke tunnel. The investigation studied the utility of the N.A.C.A. smoke tunnel as applied to reducing the drag of objects for … more
Date: December 1933
Creator: Jacobs, Eastman N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Rolling, yawing, and hinge moments produced by rectangular ailerons

Description: Ailerons described in references 1, 2, and 3, are summarized in the form of empirical equations which relate the aileron dimensions and displacements to the rolling, yawing, and hinge moments for pitch angles of 0 and 12 degrees, corresponding to angles of attack of the wings of 4 and 16 degrees, respectively.
Date: January 1933
Creator: Heald, R. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Simplified aerodynamic analysis of the cyclogiro rotating wing system

Description: A simplified aerodynamic theory of the cyclogiro rotating wing is presented herein. In addition, examples have been calculated showing the effect on the rotor characteristics of varying the design parameters of the rotor. A performance prediction, on the basis of the theory here developed, is appended, showing the performance to be expected of a machine employing this system of sustentation. The aerodynamic principles of the cyclogiro are sound; hovering flight, vertical climb, and a reasonable… more
Date: August 1933
Creator: Wheatley, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Characteristics of Sprays Obtained from Pintle-Type Injection Nozzles

Description: "This report presents the results of tests made with the pintle-type injection nozzles, one having a pintle angle of 8 degrees, the other a pintle angle of 30 degrees. The fuel was injected into a glass-windowed pressure chamber and the spray photographed by means of the N.A.C.A. spray photography apparatus. Curves are presented that give the penetration of the spray tips when fuel oil is injected by pressures of 1,500 to 4,000 pounds per square inch into air at room temperature and densities o… more
Date: July 1933
Creator: Marsh, E. T. & Waldron, C. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Strength Tests of Thin-Walled Duralumin Cylinders in Pure Bending

Description: "This report is the third of a series presenting the results of strengths tests on thin-walled cylinders and truncated cones of circular and elliptic section; it includes the results obtained from pure bending tests on 58 thin-walled duralumin cylinders of circular section with ends clamped to rigid bulkheads. The tests show that the stress on the extreme fiber at failure as calculated by the ordinary theory of bending is from 30 to 80 percent greater than the compressive stress at failure for … more
Date: December 1933
Creator: Lundquist, Eugene E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A study of factors affecting the steady spin of an airplane

Description: Data from wind-tunnel tests on a model of the NY-1 airplane were used in a study of the effect on the steady spin of a number of factors considered to be important. The factors were of two classes, mass distribution effects and aerodynamic effects. The study indicated that mass extended along the longitudinal axis has no detrimental effect or is even slightly beneficial, mass extended along the lateral axis is detrimental if the airplane spins with the inner wing tip far down, and mass extended… more
Date: August 1933
Creator: Scudder, Nathan F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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