Technical Report Archive & Image Library (TRAIL) - 30 Matching Results

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Aerodynamic Characteristics of a 4-Engine Monoplane Showing Comparison of Air-Cooled and Liquid-Cooled Engine Installations

Description: From Introduction: "An investigation has been conducted in the N.A.C.A. full-scale wind tunnel to determine the aerodynamic characteristics of a 1/4-scale model of a 4-engine monoplane when equipped with comparable air-cooled engine and liquid-cooled engine installations. The air-cooled engine installation consisted of nacelles equipped with N..A.C.A. cowlings and oil coolers located in the leading edge of the wing."
Date: July 1939
Creator: Silverstein, Abe & Wilson, Herbert A., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Blade Design Data for Axial-Flow Fans and Compressors

Description: Report presenting an investigation to obtain blade design data for high-efficiency axial-flow fans and compressors, which were carried out in a two-dimensional low-speed cascade tunnel. The effects of camber, solidity, and stagger on blade turning angle and the shape of pressure distributions were determined for a family of five low-drag airfoils.
Date: July 1945
Creator: Bogdonoff, Seymour M. & Bogdonoff, Harriet E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calibrations of pitot-static tubes at high speeds

Description: Report presenting the calibrations of three types of service pitot-static tubes over an approximate range of speeds of 150 to 600 miles per hour. The calibrations indicated a need for a pitot-static tube with greater accuracy, especially at higher speeds. Results regarding the service tubes, Prandtl tube, Eigh-speed tube, and a comparison of the tubes are provided.
Date: July 1942
Creator: Hensley, Reece V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling Tests of an Air-Cooled Engine Cylinder With Copper Fins on the Barrel

Description: Report presenting the results of comparative cooling tests run on two Wright C9GC (G-200) cylinders, one with the original steel fins and one with 1-inch spiral copper fins brazed on the barrel. Calculations were also performed using copper and aluminum fins with the same weight as the original steel fins, which showed positive results. Results regarding cylinder-temperature correlation, piston-temperature correlation, and comparative performance are also provided.
Date: July 1942
Creator: Sanders, J. C.; Wilsted, H. D. & Mulcahy, B. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Design charts for cross-flow tubular intercoolers charge-through-tube type

Description: Report presenting equations relating the various dimensions, air weight flow, and performance of a cross-flow tubular intercooler in which the charge flows through and the cooling air across the tubes. A method of determining and presenting the performance of a given intercooler at various operating conditions is indicated. Results regarding the cooling effectiveness equation, effect of primary intercooler variables, design charts, effect of tube arrangement on intercooler characteristics, and … more
Date: July 1941
Creator: Reuter, J. George & Valerino, Michael F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of General Relations for the Behavior of Turbulent Boundary Layers

Description: Report presenting an analysis of data for turbulent boundary layers along wings and bodies of various shapes in order to determine the fundamental variables that control the development of turbulent boundary layers. Results indicate that the type of velocity distribution in the boundary layer could be expressed in terms of a single parameter.
Date: July 1943
Creator: von Doenhoff, Albert E. & Tetervin, Neal
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The development and application of high-critical-speed nose inlets

Description: From Summary: "An analysis of the nose-inlet shapes developed in previous investigations to represent the optimum from the standpoint of critical speed has shown that marked similarity exists between the nondimensional profiles of inlets which have widely different proportions and critical speeds. With the nondimensional similarity of such profiles established, the large differences in the critical speeds of these nose inlets must be a function of their proportions. An investigation was underta… more
Date: July 1945
Creator: Baals, Donald D.; Smith, Norman F. & Wright, John B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Drag Measurements of a Protruding 0.50-Caliber Machine Gun

Description: Report presenting drag and cross-wind force measurements of a Browning 0.50-caliber M2 machine gun at a range of air speeds in the NACA wind tunnel. The gun protruded through the top of the tunnel wall into the air stream and tests were performed at a variety of angles in order to determine the power required to turn the gun against the aerodynamic forces and the horsepower absorbed in air drag by the protruding gun. Special attention is given to the jacket around the gun, which seems to provid… more
Date: July 1941
Creator: Luoma, Arvo A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Compressibility on Pressure Distribution Over an Airfoil With a Slotted Frise Aileron

Description: Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 Mach at various angles of attack and aileron defections. Section characteristics were determined from these pressure data. Results indicated loss of aileron rolling power for deflections ranging from -12 Degrees to -19 Degrees.
Date: July 1944
Creator: Luoma, Arvo A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The effect of external shape upon the drag of a scoop

Description: Report presenting testing of six scoops built using the principles of NACA cowling design to show the advantage of using those principles. Three scoops had a good nose contour with different afterbody lengths and three were of inferior nose shape. Results regarding drag, cooling pressure, and surface pressure survey are provided.
Date: July 1941
Creator: Naiman, Irven & Hill, Paul R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of leakage past aileron nose on aerodynamic characteristics of plain and internally balanced ailerons on NACA 66(215)-216, a = 1.0 airfoil

Description: Report presenting an investigation in two-dimensional flow to determine the effect of leakage past the aileron nose on the aerodynamic characteristics of ailerons. The effects of amount and type of leakage, aileron contour, and Mach and Reynolds number are investigated.
Date: July 1945
Creator: Bird, J. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of the Lift Coefficient on Propeller Flutter

Description: Report presenting flutter of propellers at high angles of attack and flutter data obtained in connection with tests of models of large wind-tunnel propellers. The stall flutter speed was found to be much lower than the calculated classical flutter speed. That flutter speed is only obtainable if the propeller operates at the ideal angle of zero twist.
Date: July 1945
Creator: Theodorsen, Theodore & Regier, Arthur A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Estimation of Pressure Distributions at Subcritical Speeds for Turrets Located on a Wing

Description: Report presenting the use of current methods that include interference and compressibility effects to estimate pressures over and near turrets located on a wing in regions of high interference velocities. The agreement between measured and estimated pressures indicated that present methods are adequate for predicting approximate critical speeds and for estimating loads at subcritical speeds with sufficient accuracy for design purposes.
Date: July 1944
Creator: Ritchie, Virgil S. & Daniels, Everett J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of Compressibility Effects on a Three-Blade Thin Clark Y Propeller Operating at Constant Advance-Diameter Ratio and Blade Angle

Description: Report presenting flight tests of a three-blade thin Clark Y propeller operating at a fixed blade angle of approximately 46.8 degrees at 0.75 radius, at an advance-diameter ratio of 2.37, and at true airplane speeds of approximately 300 and 450 miles per hour. Comparisons of the results at the two different speeds indicated losses in propeller efficiency from 11 to 18 percent at high speed. Report is incomplete.
Date: July 1943
Creator: Vogeley, A. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

High-Speed Wind-Tunnel Tests of Gun Openings in the Nose of the Fuselage of a 1/4-Scale Model

Description: "In connection with recent tests of a 1/4-scale model pursuit airplane in the NACA 8-foot high-speed tunnel, gun openings having low drag were developed for installation in the nose of the fuselage. The increase in the fuselage-drag coefficient for the final form of openings was 0.0132 at a Mach number of 0.69 and at an angle of attack of 0 degrees. The corresponding drag coefficient based on the wing area was about 0.0005. The critical speed of the airplane was not affected by the gun openings… more
Date: July 1942
Creator: Fedziuk, Henry A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The knock-limited performance of several miscellaneous fuels blended with a base fuel

Description: Report presenting investigations to determine the knock-limited performance of blends of 90 percent by volume AN-F-28, Amendment-2 fuel, and 10 percent by volume of the following fuels: tert-amyl alcohol, 2,6-dimethyl-1, 4-dioxane, methyl tert-butyl ether, methyl tert-butyl ketone, methyl isobutyl ketone, mesityl oxide, acetone, and diisopropyl ketone.
Date: July 1944
Creator: Bellman, Donald R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Method for the Rapid Estimation of Turbulent Boundary-Layer Thickness for Calculating Profile Drag

Description: "An analysis is developed that makes it possible to integrate von Kármán's boundary-layer momentum equation directly. For this purpose, the skin friction coefficient is expressed as a function of the Reynolds number based on the boundary-layer momentum thickness and the boundary-layer shape is assumed to be constant. The integrated equation permits the boundary-layer momentum thickness at the airfoil trailing edge to be rapidly determined for the estimation of airfoil profile-drag coefficients"… more
Date: July 1944
Creator: Tetervin, Neal
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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NACA Mach number indicator for use in high-speed tunnels

Description: Report presenting a description of a device for indicating stream Mach number in a high-speed tunnel. It consists of a mechanism for determining the pressure ratio that Mach number is a function of. The instrument is in service in the 8-foot high-speed tunnel and its accuracy has been found adequate for wind-tunnel requirements.
Date: July 1943
Creator: Smith, Norman F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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NACA Mach Number Warning Device for Use in Flight

Description: Report presenting an instrument for warning the pilot of the approach of the airplane to critical speed conditions. The device closes a contact that completes the electrical circuit of a suitable warning indicators when a predetermined limiting Mach number is approached. It can be used to operate any electrical apparatus through the use of suitable relays.
Date: July 1944
Creator: Goodman, Jerry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Paths of target-seeking missiles in two dimensions

Description: Report presenting a discussion of some of the parameters that enter into the equation of the path of a missile which is pursuing its target. The missile is assumed to be guided by a target seeker that might be employed in any one of several ways. Results regarding the normal-pursuit navigation, constant navigation, proportional navigation, line-of-sight navigation, and effect of angle of attack and sideslip are provided.
Date: July 1946
Creator: Watkins, Charles E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Paths of Target Seeking Missiles in Two Dimensions

Description: Parameters that enter into equation of trajectory of a missile are discussed. Investigation is made of normal pursuit, of constant, proportional, and line--of-sight methods of navigation employing target seeker, and of deriving corresponding pursuit paths. Pursuit paths obtained under similar conditions for different methods are compared. Proportional navigation is concluded to be best method for using target seeker installed in missile.
Date: July 1946
Creator: Watkins, Charles E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation in the NACA Low-Turbulence Tunnel of Low-Drag Airfoil Sections Suitable for Admitting Air at the Leading Edge

Description: From Summary: "An investigation was carried out in the NACA low-turbulence tunnel to develop low-drag airfoil sections suitable for admitting air at the leading edge. A thickness distribution having the desired type of pressure distribution was found from tests of a flexible model. Other airfoil shapes were derived from this original shape by varying the thickness, the camper, the leading-edge radius, and the size of the leading-edge opening. Data are presented giving the characteristics of the… more
Date: July 1942
Creator: von Doenhoff, Albert E. & Horton, Elmer A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A preliminary investigation of exhaust-gas ejectors for ground cooling

Description: Report presenting a preliminary investigation to determine the suitability of ejectors actuated by the exhaust of a radial air-cooled aircraft engine for providing engine cooling air at the ground condition. Various length and diameter ejectors were tested for varying engine power for nine ejectors actuated by the exhaust of individual cylinders and three ejectors actuated by the exhaust of groups of three cylinders.
Date: July 1942
Creator: Manganiello, Eugene J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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