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Wall interference in a two-dimensional-flow wind tunnel with consideration of the effect of compressibility

Description: Report presenting tunnel-wall corrections for an airfoil of finite thickness and camber in a two-dimensional-flow wind tunnel. The theory takes account of the effects of the wake of the airfoil and of the compressibility of the fluid and is based on the assumption that the chord of the airfoil is small in comparison with the height of the tunnel. The theoretical results are compared with the small amount of low-speed experimental data available and agreement is seen to be satisfactory, even for relatively large values of the chord-height ratio.
Date: December 1944
Creator: Allen, H. Julian & Vincenti, Walter G.
Partner: UNT Libraries Government Documents Department

Trends in surface-ignition temperatures

Description: Report discusses the variation of surface-ignition temperature with charge density, fuel-air ratio, and surface-ignition advance. Tests on several fuels were conducted on a supercharged CFR engine to determine surface-ignition temperature as a function of the three variables. It was concluded that surface-ignition temperature is not a satisfactory criterion for differentiating between preignition characteristics of different fuels.
Date: September 1944
Creator: Alquist, Henry E. & Male, Donald W.
Partner: UNT Libraries Government Documents Department

A correlation of the effects of compression ratio and inlet-air temperature on the knock limits of aviation fuels in a CFR engine 2

Description: Report presenting the knock-limited performance of nine fuels comprising isolated members of four classes of hydrocarbons in the form of three-dimensional plots of fuel-air ratio, compression temperature, and compression-air density.
Date: June 1946
Creator: Alqusit, Henry E.; O'Dell, Leon & Evvard, John C.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Control-Surface Characteristics 3: A Small Aerodynamic Balance of Various Nose Shapes Used With a 30-Percent-Chord Flap on an NACA 0009 Airfoil

Description: Report presenting tests in the 4- by 6-foot vertical wind tunnel of an NACA 0009 airfoil with a 30-percent-chord flap with a small amount of aerodynamic balance. In the investigation, the effect of balance nose shape and gap at the nose of the flap has been determined. The results indicate that, in general, the lift effectiveness of the flap was unaffected by the addition of a small amount of aerodynamic overhang, and the balance effectiveness of the flap was increased.
Date: August 1941
Creator: Ames, Milton B., Jr.
Partner: UNT Libraries Government Documents Department

Wind-Tunnel Investigation of Control-Surface Characteristics 4: A Medium Aerodynamic Balance of Various Nose Shapes Used With a 30-Percent-Chord Flap on an NACA 0009 Airfoil

Description: Report presenting tests made in the 4- by 6-foot vertical wind tunnel of an NACA 0009 airfoil with a 30-percent-chord flap with a medium amount of aerodynamic overhanging balance. In this investigation, the effects of the shape of the flap-nose overhang and the gap at the nose of the flap have been determined. The results indicate that, generally, the lift effectiveness of the aerodynamically balanced flap was increased slightly over that of a plain flap when a blunt or medium flap nose was used on the balanced flap.
Date: September 1941
Creator: Ames, Milton B., Jr. & Eastman, Donald R., Jr.
Partner: UNT Libraries Government Documents Department

A theoretical analysis of the effect of aileron inertia and hinge moment on the maximum rolling acceleration of airplanes in abrupt aileron rolls

Description: Report presenting data on the rolling accelerations of airplanes of different types and sizes in abrupt aileron rolls in connection with a number of maneuverability and flying qualities investigations. An analysis was made to determine the relation between the torque applied to the aileron system by the pilot, the motion of the system, and the subsequent rolling motion of the airplane in abrupt aileron roll.
Date: February 1942
Creator: Bailey, F. J., Jr. & O'Sullivan, William J.
Partner: UNT Libraries Government Documents Department

Flight investigation of the performance and cooling characteristics of a long-nose high-inlet-velocity cowling on the XP-42 airplane

Description: Report presenting the results of a series of flight tests of the maximum speed and cooling characteristics in high-speed level flight and in climb of the XP-42 airplane equipped with a long-nose high-inlet-velocity cowling. The results indicated that a maximum speed of 338 miles per hour at 870 horsepower at 17,000 feet was achievable, which is above the engine critical altitude. Pressure measurements in the entrances in the cylinder baffles showed a uniform distribution of pressure on the front of the engine in high-speed level flight and a fairly uniform distribution in full-power climb.
Date: April 1942
Creator: Bailey, F. J., Jr.; Johnston, J. Ford & Voglewede, T. J.
Partner: UNT Libraries Government Documents Department

Lead susceptibility of paraffins, cycloparaffins, and olefins

Description: "General relationships for the lead susceptibilities of paraffins, cycloparaffins, and olefins are presented. Methods are described by which the lead response may be estimated for these hydrocarbon classes, whether the lead response is indicated by octane number, critical compression ratio, or indicated mean effective pressure as limited by knock" (p. 1).
Date: May 1943
Creator: Barnett, Henry C.
Partner: UNT Libraries Government Documents Department

Wind-tunnel tests of a dual-rotating propeller having one component locked or windmilling

Description: From Summary: "The effect on the propulsive efficiency of locking or windmilling one propeller of a six-blade dual-rotating propeller installation was determined in the Langley propeller-research tunnel. Tests were made of both pusher and tractor configurations, with the unpowered propeller both leading and following the powered propeller, which was set at a blade angle of 40 degrees. The maximum propulsive efficiency of the powered propeller in combination with the locked or windmilling propeller was, in all cases, lower than that of the powered propeller operating alone."
Date: January 1945
Creator: Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department

Tensile Tests of NACA and Conventional Machine-Countersunk Flush Rivets

Description: An investigation was conducted to determine and compare the tensile strength of NACA and conventional machine-countersunk flush rivets of several rivet-head angles and varying countersunk depth. The results of the investigation are presented in the form of curves that show the variation of the tensile strength of the rivet with the ratio of the sheet thickness to the rivet diameter. For the same rivet-head angle and for a given angle of c/d, the NACA rivets developed higher tensile strength than the conventional rivets.
Date: October 1944
Creator: Bartone, Leonard M. & Mandel, Merven W.
Partner: UNT Libraries Government Documents Department

Critical combinations of shear and transverse direct stress for an infinitely long flat plate with edges elastically restrained against rotation

Description: Report presenting an exact solution and a closely concurring approximate energy solution for the buckling of an infinitely long flat plate under combined shear and transverse direct stress with edges elastically restrained against rotation. An appreciable fraction of the critical stress in pure shear may be applied to the plate without any reduction in the transverse compressive stress necessary to produce buckling.
Date: January 1945
Creator: Batdorf, S. B. & Houbolt, John C.
Partner: UNT Libraries Government Documents Department

Critical Combinations of Longitudinal and Transverse Direct Stress for an Infinitely Long Flat Plate With Edges Elastically Restrained Against Rotation

Description: Report presenting a theoretical investigation of the buckling of an infinitely long flat plate with edges elastically restrained against rotation under combinations of longitudinal and transverse direct stress. Interaction curves are presented that give the critical combinations of stress for several different degrees of elastic edge restraint, including simple support and complete fixity.
Date: March 1946
Creator: Batdorf, S. B.; Stein, Manuel & Libove, Charles
Partner: UNT Libraries Government Documents Department

Aerodynamic tests of a full-scale TBF-1 aileron installation in the Langley 16-foot high-speed tunnel

Description: From Summary: "This report describes tests in the Langley 16-foot high-speed tunnel to determine whether these failures could be attributed to changes in the aerodynamic characteristics of the ailerons at high speeds."
Date: December 1944
Creator: Becker, John V. & Korycinski, Peter F.
Partner: UNT Libraries Government Documents Department

Continuous use of internal cooling to suppress knock in aircraft engines cruising at high power

Description: Report presenting an investigation of the possibility of using internal cooling instead of fuel enrichment to suppress knock and to estimate the fuel savings that will result. Data from four different sources was examined and an analysis of the fuel consumption was conducted. Four different types of coolants were explored.
Date: August 1944
Creator: Bell, Arthur H.
Partner: UNT Libraries Government Documents Department

A Preliminary Investigation of the Characteristics of Air Scoops on a Fuselage

Description: Report presenting an investigation of the characteristics of air scoops in the NACA propeller-research tunnel. The investigation showed that, at inlet-velocity ratios equal to or greater than 0.3, scoops in a forward position on the fuselage gave total pressures in the inlet nearly equal to free-stream total pressure.
Date: December 1942
Creator: Bell, E. Barton & DeKoster, Lucas J.
Partner: UNT Libraries Government Documents Department

Test of a Dual-Rotation Axial-Flow Fan

Description: Report presenting a dual-rotation axial-flow fan composed of two oppositely rotating 24-blade rotors. The fan was tested with various combinations of front and rear blade angles and with two combinations of front and rear solidities. For quantity coefficients above 0.3 the greatest pressure rise was obtained from 24 blades in each rotor with the blades adjusted to absorb equal torque at maximum pressure.
Date: December 1942
Creator: Bell, E. Barton & DeKoster, Lucas J.
Partner: UNT Libraries Government Documents Department

The Effect of Solidity, Blade Section, and Contravane Angle on the Characteristics of an Axial-Flow Fan

Description: Report presenting an axial flow fan tested with 5, 9, 12, 18, and 24 blades and with two different blade sections. The range of contravane angle and blade angle without contravanes was extended past results published for the same fan previously.
Date: December 1942
Creator: Bell, E. Barton & Dekoster, Lucas J.
Partner: UNT Libraries Government Documents Department

The Effects of Angle of Dead Rise and Angle of Afterbody Keel on the Resistance of a Model of a Flying-Boat Hull

Description: Report presenting a series of models of flying-boat hulls tested to determine the effects of the angle of dead rise and the angle of afterbody keel on resistance and spray characteristics. Three angles of dead rise and three angles of afterbody keel were investigated. The results are expressed in nondimensional coefficients.
Date: February 1943
Creator: Bell, Joe W. & Willis, John M., Jr.
Partner: UNT Libraries Government Documents Department

Effect of Length-Beam Ration on Resistance and Spray of Three Models of Flying-Boat Hulls

Description: Report presenting an investigation of the effect of changes in the length-beam ratio of flying-boat hulls on resistance and spray. A family of three models of hulls of different length-beam ratios was used and, in order to maintain comparable hull sizes, the plan-form areas of the hulls were made approximately equal by keeping equal products of length and beam. Results regarding resistance, spray, and take-off performance are provided.
Date: October 1943
Creator: Bell, Joe W.; Garrison, Charlie C. & Zeck, Howard
Partner: UNT Libraries Government Documents Department

Knock-limited power outputs from a CFR engine using internal coolants 1: monomethylamine and dimethylamine

Description: Report presenting an investigation to determine the knock-limited power obtainable by injecting water solutions of monomethylamine and dimethylamine as internal coolants into a CFR engine using AN-F-28, Amendment-2, fuel.
Date: December 1944
Creator: Bellman, Donald R.; Moeckel, W. E. & Evvard, John C.
Partner: UNT Libraries Government Documents Department

An Instrument for the Determination of Rain Densities in Flight

Description: Report presenting an investigation to develop an instrument for the determination of rain densities in this range in flight. The major requirements for the instrument are ease of operation, minimum weight and bulk, rapid response, and simplicity of installation.
Date: May 1943
Creator: Bemis, John R. & Houghton, Henry G., Jr.
Partner: UNT Libraries Government Documents Department

The influence of vertical-tail design and direction of propeller rotation on trim characteristics of a twin-engine-airplane model with one engine inoperative

Description: Report presenting testing to determine the influence of propeller rotation and vertical-tail design on the trim characteristics of a model of a twin-engine airplane with one engine inoperative. The tests showed that the effect of mode of propeller rotation on the directional trim characteristics of the model operating with asymmetric power was considerable. Results regarding the effect of mode of propeller rotation and effect of vertical-tail design are provided.
Date: February 1945
Creator: Bennett, Charles V.
Partner: UNT Libraries Government Documents Department