Technical Report Archive & Image Library (TRAIL) - 20 Matching Results

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Aerodynamic Characteristics of Four Republic Airfoil Sections from Tests in Langley Two-Dimensional Low-Turbulence Tunnels

Description: "Four airfoils sections, designed by the Republic Aviation Corporation for the root and tip sections of the XF-12 airplane, were tested in the Langley two-dimensional low-turbulence tunnels to obtain their aerodynamic characteristics. Lift characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, 9,000,000, and 14,000,000, whereas drag characteristics were obtained at Reynolds numbers of 3,000,000, 6,000,000, and 9,000,000. Pressure distributions were obtained for one of the ro… more
Date: September 27, 1945
Creator: Klein, Milton M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Airfoil Section Data From Tests of 10 Practical-Construction Sections of Helicopter Rotor Blades Submitted by the Sikorsky Aircraft Division, United Aircraft Corporation

Description: Report presenting 10 practical-construction models of sections of helicopter rotor blades tested in the NACA two-dimensional low-turbulence pressure tunnel at atmospheric pressure. Lift, drag, and pitching-moment characteristics of blades representing the present method of construction of the YR-4A helicopter were determined.
Date: September 1944
Creator: Tetervin, Neal
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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Compression Tests of Six Curved Paper-Base Plastic Panels With Outward-Acting Normal Pressure

Description: Report presenting results of compression tests of six paper-base plastic panels with outward-acting normal pressure. All panels failed by separation of the skin, either from the rib or from the stiffeners. Results regarding the introduction of air pressure and types of failures encountered are provided.
Date: September 1944
Creator: Schuette, Evan H.; Rafel, Norman & Dobrowski, Charles V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Cooling of Gas Turbines, 2, Effectiveness of Rim Cooling of Blades

Description: An analysis of rim cooling, which cools the blade by condition alone, was conducted. Gas temperatures ranged from 1300 degrees to 1900 degrees F and rim temperatures from 0 degrees to 1000 degrees F below gas temperatures. Results show that gas temperature increases up to 200 degrees F are permissible provided that the blades are cooled by 400 degrees to 500 degrees F below the gas temperature. Relatively small amounts of blade cooling, at constant gas temperature, give large increases in blade… more
Date: September 20, 1945
Creator: Wolfenstein, Lincoln; Meyer, Gene L. & McCarthy, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of High-Resistance Ignition Cable on the Erosion of Spark-Plug Electrodes

Description: Report discussing testing to determine the effects that using high-resistance ignition cable has on erosion of spark-plug electrodes. Erosion was found to be reduce about 70 percent when high-resistance ignition cable was used in place of standard cable.
Date: September 1945
Creator: Swett, Clyde C., Jr. & Rodgers, Franklin A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Maximum Cruise-Power Operation at Ultra-Lean Mixture and Increased Spark Advance on the Mechanical Condition of Cylinder Components

Description: "A continuous 50-hour test was conducted to determine the effect of maximum cruise-power operation at ultra-lean fuel-air mixture and increased spark advance on the mechanical conditions of cylinder components. The test was conducted on a nine-cylinder air-cooled radial engine at the following conditions:brake horsepower, 750; engine speed, 1900 rpm; brake mean effective pressure, 172 pounds per square inch; fuel-air ratio, 0.052; spark advance, 30 deg B.T.C.; and maximum rear-spark-plug-bushin… more
Date: September 27, 1945
Creator: Harris, Herbert B.; Duffy, Robert T. & Erwin, Robert D., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Water Injection on Knock-Limited Performance of a V-Type 12-Cylinder Liquid-Cooled Engine

Description: Report presenting an investigation conducted to determine the effect of water injection on the knock-limited performance of a V-type 12-cylinder liquid-cooled engine. The knock-limited performance tests were made at an engine speed of 3000 rpm with carburetor-air temperatures of 158, 101, and 50 degrees Fahrenheit at water-fuel ratios of 0, 0.2, 0.4, and 0.6.
Date: September 1944
Creator: Harries, Myron L.; Nelson, R. Lee & Berguson, Howard E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Xylidines on the Load-Carrying Capacity of an Aircraft Engine Oil - 2

Description: Report presenting testing of the effect of xylidines on the load-carrying capacity of an aircraft-engine oil in several test devices. There is also interest in the suitability of xylidines as an antiknock component in aviation gasoline, so xylidines were added to the gasoline mixes used in several different machines.
Date: September 1943
Creator: Olson, Walter T. & Spurr, Robert A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Measurements of the Lateral Control Characteristics of an Airplane Equipped With a Combination Aileron-Spoiler Control System

Description: Report presenting flight tests conducted to measure the lateral-control characteristics of an airplane, equipped with a lateral-control system, in which as the flaps are lowered the ailerons droop and a gradual transition of lateral control from ailerons to spoilers takes place. The variation of maximum rolling velocity with lateral stick movement as obtained in abrupt rudder-locked rolls was satisfactorily smooth except when control was by spoiler alone.
Date: September 2, 1942
Creator: Clousing, Lawrence A. & McAvoy, William H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flutter tests of B-34 fin-rudder-tab system

Description: From Summary: "Tests on the B-34 fin-rudder-tab assembly were performed in the NACA 8-foot high-speed tunnel. Two cases of tab flutter were studied. It was shown conclusively that the frequency of the original or heavy tab was too low and caused coupling with one of the lower bending frequencies. A general conclusion was made that the tab frequency should be considerably higher than the lower modes of the fin-rudder assembly because there is generally a weaker coupling between the tab and the h… more
Date: September 1944
Creator: Theodorsen, Theodore
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Longitudinal characteristics and aileron effectiveness of a midwing airplane from high-speed wind tunnel tests

Description: Report presenting wind-tunnel tests of a 0.175-scale model of a midwing airplane in order to determine the high-speed longitudinal characteristics, to test devices for improving longitudinal control at high Mach numbers, and to determine the aileron effectiveness at high Mach numbers. Force and moment coefficients are computed from test data. Control forces, elevator angle, and aileron angle for several flight conditions are predicted.
Date: September 29, 1944
Creator: Hall, Charles F. & Mannes, Robert L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements in Flight of the Lateral-Control Characteristics of an Airplane Equipped with Full-Span Zap Flaps and Simple Circular-Arc-Type Ailerons

Description: Flight tests were conducted on the OS2U-2 seaplane with simple circular-arc-type ailerons directly connected to the actuating torque tube. Two aileron test installations were made, differing only in the inclination of the projecting surface with the wing's upper surface. The lateral-control characteristics of the airplane were determined from data obtained in stalls and rudder-fixed aileron rolls. The revised ailerons were deficient in maximum rolling effectiveness, but were capable of controll… more
Date: September 1944
Creator: Spahr, J. Richard & Christophersen, Don R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Measurements of the flying qualities of a Bell P-39D-1 airplane (AAF NO. 41-28378)

Description: Report discussing an investigation of the flight qualities of the Bell P-39D-1 airplane. Information about the longitudinal stability and control characteristics, lateral and directional stability and control, stalling characteristics, and control friction is provided.
Date: September 21, 1943
Creator: Johnson, Harold I.; Liddell, C. J. & Hoover, H. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Lift and Drag Measurements of Two Configurations of a Nacelle and Oil-Cooler Scoop for the Hughes-Kaiser Cargo Airplane

Description: Report presenting tests in the two-dimensional low-turbulence tunnel to determine the drag characteristics of two configurations of a 0.0476-scale nacelle and oil-cooler scoop for the Hughes-Kaiser cargo airplane. The nacelles were found to have a slightly favorable effect on the maximum lift coefficient.
Date: September 1943
Creator: Quinn, John H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A study of the effect of aftercooling on the power and the weight of a 2000-horsepower air-cooled engine installation

Description: Report presenting a study of the effect of aftercooling on the brake horsepower, weight, and weight-power ratio of a power plant consisting of a 2000-horsepower air-cooled engine, an intercooler, and two stages of supercharging. Three cases are considered: inadequate supercharging, supercharging to constant manifold pressure, and supercharging to detonation-limited manifold pressure.
Date: September 1944
Creator: Wood, George P. & Brimley, D. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of a 0.30 scale semispan model of the Douglas XTB2D-1 airplane wing and fuselage combination in the NACA 19-foot pressure tunnel 1: full-span flap and air-brake investigation

Description: Report presenting testing in the 19-foot pressure tunnel of a scale semispan model of the XTB2D-1 airplane wing and fuselage combination. The purpose of the investigation was to determine the optimum position of the double-slotted flap, the characteristics of the full-span flaps at various deflections in their fully extended position, the effectiveness of deflecting the full-span flaps to small positive angles as a camber changing feature, the stalling characteristics of the wing, and the effec… more
Date: September 1944
Creator: Ashworth, C. Dixon; Spooner, Stanley H. & Russell, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of a 0.30-scale semispan model of the Douglas XTB2D-1 airplane wing and fuselage combination in the NACA 19-foot pressure tunnel 2: roll-flap positioning and lateral-control investigation

Description: Report presenting testing of a scale semispan model of the Douglas XTB2D-1 airplane wing and fuselage combination equipped with full-span double-slotted flaps conducted in the 19-foot pressure tunnel. This paper describes the development of the outboard flap, or roll flap, including the determination of optimum relative position of various parts of the airplane, determination of the roll-flap loads and hinge moments for design information, and an estimation of the lateral-control forces of the … more
Date: September 1944
Creator: Spooner, Stanley H.; Ashworth, C. Dixon & Russell, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tests of a 1/40-Scale Wing-Hull Model and a 1/10-Scale Float-Strut Model of the Hughes-Kaiser Cargo Airplane in the Two-Dimensional Low-Turbulence Pressure Tunnel

Description: Report presenting aerodynamic and hydrodynamic tests of a 1/10-scale wing-hull model and a 1/10-scale float-strut model of the proposed arrangement of the Hughes-Kaiser cargo airplane. The aerodynamic tests were made primarily to study the drag characteristics of these models as originally designed and to determine how the design could be improved. Results regarding the wing-hull model and float-strut model are provided.
Date: September 1943
Creator: Fullmer, Felicien F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Bell XP-63 Low-Drag Wing Model With Split Flap

Description: Report presenting tests on the Bell XP-63 wing root section fitted with an 0.18c split flap hinged at approximately 0.805c on the lower surface. The tests were conducted to determine the effect of a 10 degree deflection of the split flap on the drag characteristics of the model at low lift coefficients.
Date: September 1941
Creator: Underwood, W. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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