National Advisory Committee for Aeronautics (NACA) - 1,263 Matching Results

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An Automatically Variable Control Linkage and Its Effect on the Lateral-Control Characteristics of a High-Speed Fighter Airplane

Description: Report discusses an analysis and preliminary design of a control linkage that varies automatically with dynamic pressure. The advantages of the device, including greater lateral control than a fixed control linkage without additional aerodynamic balance, are detailed. The effect of variable linkage on lateral-control characteristics is also described.
Date: May 1944
Creator: Gillis, Clarence L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The belt method for measuring pressure distribution

Description: "The measurement of pressure distribution may be accomplished rapidly for any number of locations deemed necessary in model or full-scale investigations by use of the 'belt' method. Reasonable accuracy may be obtained by careful use of this method" (p. 1).
Date: February 1943
Creator: Corson, Blake W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bending and Shear Stresses Developed by the Instantaneous Arrest of the Root of a Cantilever Beam Rotating With Constant Angular Velocity About a Transverse Axis Through the Root

Description: From Summary: "A theoretical investigation was made of the behavior of a cantilever beam in rotational motion about a transverse axis through the root determining the stresses, the deflections, and the accelerations that occur in the beam as a result of the arrest of motion. The equations for bending and shear stress reveal that, at a given percentage of the distance from root to tip and at a given trip velocity, the bending stresses for a particular mode are independent of the length of the be… more
Date: June 1945
Creator: Stowell, Elbridge Z.; Schwartz, Edward B. & Houbolt, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bending and Shear Stresses Developed by the Instantaneous Arrest of the Root of a Cantilever Beam With a Mass at Its Tip

Description: Report discusses an investigation into the behavior of a cantilever beam in transverse motion with a mass at its tip when the root is suddenly brought to rest. Equations for determining the stresses, deflections, and accelerations that arise in the beam are also provided. This testing can be applied to the shock created in an airplane when landing and the vibrations that result.
Date: November 1944
Creator: Stowell, Elbridge Z.; Schwartz, Edward B.; Houbolt, John C. & Schmieder, Albert K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bending and Shear Stresses Developed by the Instantaneous Arrest of the Root of a Moving Cantilever Beam

Description: Report presenting a theoretical and experimental investigation of the behavior of a cantilever beam in transverse motion when its root is suddenly brought to rest. The results of both types of investigations are compared.
Date: November 1944
Creator: Stowell, Elbridge Z.; Schwartz, Edward B. & Houbolt, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Bibliography and Review of Information Relating to the Hydrodynamics of Seaplanes

Description: Report presenting a bibliography and review of information related to the hydrodynamics of seaplanes. Characteristics of conventional hulls and floats are discussed to show the effects upon performance of changes in design parameters like dead rise, depth of step, and angle of afterbody keel. Other topics include floats, lateral stabilizers, aerodynamic and propulsive considerations, unconventional configurations, hydrofoils, and piloting and handling.
Date: September 1945
Creator: Benson, James M. & Bidwell, Jerold M.
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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Boundary-Layer Transition on the N.A.C.A. 0012 and 23012 Airfoils in the 8-Foot High-Speed Wind Tunnel

Description: Report presenting determinations of boundary-layer transition on the NACA 0012 and 23012 airfoils in the high-speed wind tunnel over a range of Reynolds numbers. For all of the lift coefficients that testing occurred at, transition occurred in the region of estimated laminar separation at low Reynolds numbers and approached the point of minimum static pressure as a forward limit at high Reynolds numbers.
Date: January 1940
Creator: Becker, John V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Breaking Aircraft-Engine Oil Foams by Use of Electrically Charged Condenser Plates

Description: Report presenting a determination of the effectiveness of a charged condenser for breaking oil foams and to obtain data on which to base the design of such a device for mounting at the oil-tank inlet of an airplane. Results regarding the condenser-plate area and arrangement, wet-plate design, condenser voltage, oil temperature, water in oil, and some safety considerations are provided.
Date: November 1944
Creator: Pinkel, I. Irving
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculated and measured turning performance of a Navy F2A-3 airplane as affected by the use of flaps

Description: Report presenting results of flight tests to determine the turning performance of a Navy F2A-3 airplane over a range of speeds for three flap deflections at two altitudes. The results are correlated with an analytical study of turning performance in which the effect of thrust on maximum lift coefficient was considered.
Date: September 1943
Creator: Clousing, Lawrence A.; Gadeberg, Burnett L. & Kauffman, William M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculated effects of full-span slotted and Fowler flaps on longitudinal stability and control characteristics for a typical fighter-type airplane with various tail modifications

Description: Report presenting an analytical study of the influence of full-span slotted and Fowler flaps on the requirements for horizontal tail surfaces. The elevator deflection required to land at three-point attitude, elevator deflection required to stall the airplane at altitude, and permissible center-of-gravity range have been calculated for a fighter-type airplane.
Date: July 1942
Creator: Goranson, R. Fabian
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of Stick Forces for an Elevator With a Spring Tab

Description: "Formulas for the calculation of hinge-moment characteristics of an elevator with a spring tab have been developed in terms of basic aerodynamic parameters, spring stiffness, and airspeed. The formulas have been used in a study of the stick-force gradients on a pursuit airplane equipped with an elevator with a spring tab. Charts are presented showing the variation of stick-force gradient in accelerated flight over a large range of speed and the complete range of spring stiffness for various cen… more
Date: June 1944
Creator: Greenberg, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of tab characteristics for flight conditions from wind-tunnel data

Description: Report presenting tail-surface characteristics calculated from wind-tunnel data, which have been reported to not correspond with flight-test measurements. The primary problem under consideration is the calculation of the effect of tab deflection on the free-floating angle of the elevator, as in a servocontrol.
Date: April 1942
Creator: Sears, Richard I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculation of the Aileron and Elevator Stick Forces and Rudder Pedal Forces for the Bell XP-83 Airplane (Project MX-511) in Spins

Description: "Aileron and elevator stick forces and rudder pedal forces for the Bell XP-83 airplane in spins have been calculated. The results indicate that the aileron and elevator stick forces may be excessive unless some suitable booster or more highly balanced control surfaces are used. The pilot will be able to move the surfaces only slightly from their normal floating locations" (p. 1).
Date: September 1945
Creator: Stone, Ralph W., Jr. & Schneiter, Leslie E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculations of Intake-Air Cooling Resulting From Water Injection and of Water Recovery From Exhaust Gas

Description: Report discussing some calculations made for the effects of water in cooling the inlet air of aircraft-engine cylinders. From Summary: "The estimates indicate that the cooling effect of the water on the inlet air can be more extensive than the cooling now obtained with the intercoolers or aftercoolers in the air-induction system. In connection with water recovery from the exhaust gas, the estimates indicate that sufficient water can be recovered from 50 percent of the exhaust gas to provide an … more
Date: August 1944
Creator: Rothrock, Addison M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculations of the Performance of a Compression-Ignition Engine-Compressor Turbine Combination 1: Performance of a Highly Supercharged Compression-Ignition Engine

Description: From Summary: "Small high-speed single-cylinder compression-ignition engines were tested to determine their performance characteristics under high supercharging. Calculations were made on the energy available in the exhaust gas of the compression-ignition engines. The maximum power at any given maximum cylinder pressure was obtained when the compression pressure was equal to the maximum cylinder pressure. Constant-pressure combustion was found possible at an engine speed of 2200 rpm."
Date: December 1945
Creator: Sanders, J. C. & Mendelson, Alexander
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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Calibrations of Service Pitot Tubes in the Langley 24-Inch High-Speed Tunnel

Description: Report discusses calibration testing performed on a Kollsman type G-1 and an NAF No. 1 pitot tube at several Mach numbers and angles of attack. The effect of drain holes on the flow within the pitot tube was analyzed and the ability to estimate the error in the total pressure was created. The accuracy of the extrapolated and estimated values were found to be within reasonable limits.
Date: February 1946
Creator: Lindsey, W. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cascade investigation of buckets for a modern aircraft turbosupercharger

Description: Report presenting a cascade investigation in two-dimensional flow in the 5-inch cascade tunnel and the 1-inch turbine-element testing apparatus to obtain a satisfactory bucket design for use in a modern aircraft turbosupercharger. Results regarding the root sections, pitch sections, and tip sections are provided.
Date: November 1944
Creator: Kantrowitz, Arthur & Erwin, John R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of beveled-trailing-edge elevators on a typical pursuit fuselage at altitudes simulating-normal flight and spin conditions

Description: Report presenting lift and elevator hinge-moment characteristics were measured on horizontal tail provided with elevators having three different beveled trailing edges. Results regarding fuselage alone and fuselage interference, lift characteristics of fuselage-tail combination, elevator hinge-moment characteristics, drag, and comparison with data from two-dimensional-flow tests are provided.
Date: December 1942
Creator: Gillis, Clarence L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of Naca 4400R Series Rectangular and Tapered Airfoils, Including the Effect of Split Flaps

Description: "At the request of the Bureau of Aeronautics, Navy Department, tests were made in the variable-density wind tunnel of a tapered wing of 3-10-18 plan form and based on the NACA 4400R series sections. The wing was also tested with 0.2 chord split flaps, deflected 60 degrees, in the center of the wing and having flat span to wing span ratios of 0.3, 0.5, 0.7, and 1.0, respectively" (p. 1).
Date: January 1941
Creator: Greenberg, Harry
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of plain and balanced elevators on a typical pursuit fuselage at attitudes simulating normal-flight and spin conditions

Description: Report presenting lift and elevator hinge-moment characteristics of a horizontal tail with various plain and balanced elevators and mounted on a typical pursuit fuselage as measured in the 7- by 10-foot wind tunnel at attitudes simulating normal-flight and spin conditions. The lift effectiveness of the elevator was practically independent of the size of the aerodynamic balance. Results regarding the fuselage alone and fuselage interference, lift characteristics of fuselage-tail combinations, li… more
Date: March 1942
Creator: Sears, Richard I. & Hoggard, H. Page, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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