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Flight and Test-Stand Investigation of High-Performance Fuels in Modified Double-Row Radial Air-Cooled Engines 1: Determination of the Cooling Characteristics of the Flight Engine

Description: Report discussing the cooling characteristics of a modified 14-cylinder double-row radial air-cooled engine installed in a four-engine airplane at a pressure altitude of 7000 feet. Testing of the variable charge-air flow, variable cooling-air pressure drop, and variable fuel-air ratio was conducted. The cooling equation, temperature-limited performance, maximum engine temperatures, and other information predicted by calculations is described.
Date: July 9, 1945
Creator: Werner, Milton; Blackman, Calvin C. & White, H. Jack
Partner: UNT Libraries Government Documents Department

Flight and Test-Stand Investigation of High-Performance Fuels in Double-Row Radial Air-Cooled Engines 2: Flight Knock Data and Comparison of Fuel Knock Limits With Engine Cooling Limits in Flight

Description: Report discussing a comparison of the antiknock characteristics of triptane with a temperature-sensitive blending agent and of the fuel knock limits with engine cooling limits. Estimates were also made of temperature-limited engine performance at several flight and engine conditions.
Date: December 30, 1944
Creator: White, H. Jack; Blackman, Calvin C. & Werner, Milton
Partner: UNT Libraries Government Documents Department

Flight and Test-Stand Investigation of High-Performance Fuels in Modified Double-Row Radial Air-Cooled Engines 2: Flight Knock Data and Comparison of Fuel Knock Limits With Engine Cooling Limits in Flight

Description: Report discussing tests on three fuels in a 14-cylinder double-row radial air-cooled engine at different engine speeds, blower ratios, and spark settings.
Date: August 4, 1945
Creator: White, H. Jack; Pragliola, Philip C. & Blackman, Calvin C.
Partner: UNT Libraries Government Documents Department

An Experimental Investigation of Flow Conditions in the Vicinity of an NACA D(Sub S)-Type Cowling

Description: Data are presented of the flow conditions in the vicinity of an NACA D sub S -type cowling. Tests were made of a 1/2 scale-nacelle model at inlet-velocity ratios ranging from 0.23 to 1.02 and angles of attack from 6 deg to 10 deg. The velocity and direction of flow in the vertical plane of symmetry of the cowling were determined from orifices and tufts installed on a board aligned with the flow. Diagrams showing velocity ratio contours and lines of constant flow angles are given.
Date: August 1946
Creator: Bryant, Rosemary P. & Boswinkle, Robert W., Jr.
Partner: UNT Libraries Government Documents Department

Tank Tests of a Powered Dynamic Model of a Flying Boat Having an Afterbody Length-Beam Ratio of 4.7-Langley Tank Model 203C-1

Description: Report discussing the results of testing on a flying boat model with an afterbody length-beam ratio of 4.7 to determine its takeoff and landing stability and resistance characteristics.The range of stable trims was smaller than models with a conventional afterbody, but the range of stable positions for the center of gravity was about the same. Landing stability was satisfactory, and the hump resistance and trim is less than a boat with a smaller ratio.
Date: October 1945
Creator: Olson, Roland E. & Haar, Marvin I.
Partner: UNT Libraries Government Documents Department

Selection of Oil Coolers to Avoid Congealing

Description: Report presenting a study of oil coolers, especially in regards to three factors: the congealing tendency of the cooler, the power cost chargeable to the installation, and the performance characteristics of the oil cooler in operation at altitude.
Date: July 1943
Creator: Martin, Dennis J.
Partner: UNT Libraries Government Documents Department

Single-Cylinder Engine Tests of Porous Chrome-Plated Cylinder Barrels With Special Bore Coatings for Radial Air-Cooled Engines

Description: Report discussing a series of single-cylinder engine tests to determine the effect of special surface coatings in porous chrome-plated cylinder barrels on oil consumption and ring wear. The coating materials were selected for their bearing and lubrication properties and on their applicability to processing. The surface coatings tested were lead overplates, silver overplates, and colloidal graphite base paint.
Date: January 1946
Creator: Johnson, Robert L. & Anderson, Roy I.
Partner: UNT Libraries Government Documents Department

Spray Characteristics and Take-Off and Landing Stability of Several Modifications of a 1/8-Size Model of the PBN-1 Flying Boat - NACA Model 192

Description: Report discussing tests on the PBN-1 airplane to determine the effects of modifications on spray characteristics and take-off and landing stability. Spray strips were found to reduce the spray over the bow at low speeds. The effects of changing the main step location and altering the elevator position are described.
Date: April 1945
Creator: Woodward, David R. & Zeck, Howard
Partner: UNT Libraries Government Documents Department

A Preliminary Theoretical Study of Helicopter-Blade Flutter Involving Dependence Upon Coning Angle and Pitch Setting

Description: "A preliminary analysis has been made of the conditions of stability of free oscillations of a hinged rotor in hovering flight. The case analyzed is a rotor with hinges allowing freedom in flapping and lagging and having a completely reversible cyclic pitch-control system, so that a twisting moment on a blade moves the control stick without hindrance from spring or friction constraint. The principal results of this study are presented in the form of a stability chart" (p. 1).
Date: July 1946
Creator: Coleman, Robert P.
Partner: UNT Libraries Government Documents Department

Performance Selection Charts for Gliders and Twin-Engine Tow Planes

Description: Report presenting performance charts for gliders and twin-engine tow planes with different degrees of aerodynamic and structural refinement. The glider charts display the gliding angle, useful load, stalling speeds, power required for level flight at various speeds, and power required for level flight while climbing at various speeds. The tow-plane charts show the stalling speeds, power required for level flight at various speeds, and power required for level flight while climbing at various speeds.
Date: May 1945
Creator: Ivey, H. Reese; Fitch, G. M. & Schultz, Wayne F.
Partner: UNT Libraries Government Documents Department

Two-Dimensional Wind-Tunnel Investigation of Two NACA Low-Drag Airfoil Sections Equipped With Slotted Flaps and a Plain NACA Low-Drag Airfoil Section for XF6U-L Airplane

Description: Report discussing the results of testing to determine the aerodynamic characteristics of three NACA-designed airfoil sections, some with flaps equipped. The tests included determination of the aerodynamic characteristics of the airfoils in smooth conditions and with standard roughness applied to the leading edge. Lift tests were also carried out at a range of flap deflections.
Date: January 1946
Creator: Loftin, Lawrence K., Jr. & Rice, Fred J., Jr.
Partner: UNT Libraries Government Documents Department

Two-Dimensional Wind-Tunnel Investigation of Spoiler Aileron Flap Model for the Hughes XF-11 Airplane

Description: Report discussing testing on a retractable spoiler aileron on the NACA 66(215)-216 airfoil with a 25-percent-chord slotted flap. The effects of spoiler thickness, spoiler gap, spoiler bevel angle, spoiler roughness, and flap deflection on aerodynamic characteristics are described.
Date: April 1945
Creator: Underwood, William J. & Fullmer, Felicien F., Jr.
Partner: UNT Libraries Government Documents Department

Two-Dimensional Wind-Tunnel Investigation of Six Airfoil Sections for the Wing of the Vega XP2V-1 Airplane

Description: Report discussing testing of six airfoil sections for the wing of the Vega XP2V-1 airplane in a smooth condition and with standard leading-edge roughness. Information about the lift, drag, pitching-moment characteristics, and sensitivity to roughness is provided. No airfoil was found to be superior to the others in all categories.
Date: October 1945
Creator: Fullmer, Felicien F., Jr.
Partner: UNT Libraries Government Documents Department

Relation Between Fuel Economy and Crank Angle for the Maximum Rate of Pressure Rise

Description: Report discussing an investigation to determine whether the crank angle for maximum rate of pressure rise can be used to indicate maximum-economy spark advance. Information about spark-advance tests at constant inlet-air pressure and fuel-air-ratio test results are provided.
Date: May 21, 1945
Creator: Cook, Harvey A. & Brightwell, Virginia L.
Partner: UNT Libraries Government Documents Department

Reduction of Fuel-Vapor Loss by Omitting Some of the Fuel Constituents Normally Lost During Flight

Description: Report discussing an investigation to determine the effect of omitting some of the fuel constituents in AN-F-28 Amendment 2 fuel that are normally lost in flight on fuel-vapor loss. Removing the components was found to decrease the fuel-vapor loss and increase the critical altitudes.
Date: August 27, 1945
Creator: Stone, Charles S. & Kramer, Walter E.
Partner: UNT Libraries Government Documents Department

Static-Thrust Investigation of Full-Scale PV-2 Helicopter Rotors Having NACA 0012.6 and 23012.6 Airfoil Sections

Description: An investigation was conducted to compare the performance of two 25-ft-diam rotors which had identical dimensions and were similar in construction but different in blade airfoil-sections. Tests were conducted at indicated blade pitch angles from 3 degrees to 11.5 degrees and rotor speeds of 200, 290, and 371 rpm. The 23012.6 rotor required 2 percent less power to hover than the 0012.6. At thrust coefficients above design, the performance of the 23012.6 became better than the 0012.6 rotor.
Date: May 1946
Creator: Lipson, Stanley
Partner: UNT Libraries Government Documents Department

Suitability of 18 Aromatic Amines for Overwater Storage When Blended With Aviation Gasoline

Description: Report discussing testing of aromatic amines as antiknock additives, and more specifically the suitability of overwater storage for these fuel blends. 12 aromatic amines of three different concentrations at two temperatures were measured. The chemical properties of the most promising fuel blends are described in more detail and correlations were noted.
Date: June 20, 1945
Creator: Goodman, Irving A. & Howard, J. Nelson
Partner: UNT Libraries Government Documents Department

Résumé of NACA Stability and Control Tests of the Bell P-63 Series Airplane

Description: Report on stability and control tests of the Bell P-63 series airplanes. Information about the spin characteristics, lateral control characteristics, longitudinal stability and control characteristics and directional stability and control characteristics is provided. A chronology of testing and detailed description of the airplane and its modifications are also provided.
Date: October 19, 1944
Creator: Johnson, Harold I.
Partner: UNT Libraries Government Documents Department

Sea-Level Performance Tests of a 22-Inch-Diameter Pulse-Jet Engine at Various Simulated Ram Pressures

Description: Report on sea-level performance tests of a 22-inch-diameter pulse-jet engine on a thrust stand. The tests were conducted at several ram pressures and the entire range of fuel flows that the engine can operate at. Information about the maximum-thrust operation, operating frequency, maximum combustion chamber pressures, and operating lives is provided.
Date: October 2, 1945
Creator: Manganiello, Eugene J.; Valerino, Michael F. & Essig, Robert H.
Partner: UNT Libraries Government Documents Department

Process of Lead-Deposit Accumulations on Aircraft-Engine Spark Plugs

Description: Report discussing an investigation of the progressive accumulation of load deposits on spark plugs under nonvarying operating conditions. Deposit-weight determinations and photographic observations are presented, and the specific characteristics of deposit accumulation are described.
Date: December 1945
Creator: Sloop, J. L.; Kinney, George R. & Rowe, William H.
Partner: UNT Libraries Government Documents Department

Smoking Characteristics of Various Fuels as Determined by Open-Cup and Laboratory-Burner Smoke Tests

Description: Report discussing tests in a combustion chamber to obtain smoking characteristics data on a variety of hydrocarbon fuels. Details about the smoking tendencies and burning rates of the fuels in uncontrolled and controlled tests are provided.
Date: {1945-06, 1945-09}
Creator: Ebersole, Earl R. & Barnett, Henry C.
Partner: UNT Libraries Government Documents Department

Some Flight Measurements on Pressure Distribution During Tail Buffeting

Description: Report presenting pressure-distribution measurements obtained from the horizontal tail surfaces of the Curtiss P-40K airplane during low-speed pull-ups to abrupt stall in which tail buffeting was experienced. The chordwise load distributions during buffeting are similar to those experienced during angle-of-attack changes. The location of the stall and frequency of stall disturbances are also described.
Date: October 1945
Creator: Boshar, John
Partner: UNT Libraries Government Documents Department

Some Notes on the Effects of Jet-Exit Design on Static Longitudinal Stability

Description: Report discussing several types of jet-exit designs, including normal, beveled, and unsymmetrical shapes, and their effect on the stability characteristics of the aircraft. No deviation of the jet center line from its exposed path is likely to be obtained if a jet exist is used that is normal to the flow. Having a tilted or asymmetrical exit was found to adversely affect the stability of the aircraft.
Date: May 1946
Creator: Gillis, Clarence L. & Weil, Joseph
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Alternative Propellers Operating Behind Deflected Wing Flaps for the XB-36 Airplane

Description: Report discussing testing on the aerodynamic characteristics of two pusher propellers with the same plan form but different airfoil sections behind a slotted flap on the XD-36 airplane. Testing was carried out over the range of blade angles and flap deflections necessary to cover all flight conditions. The effects of flaps and of tip Mach number are described in detail.
Date: December 1945
Creator: Boxer, Emanuel
Partner: UNT Libraries Government Documents Department