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The High-Speed Characteristics of Several Flaps and Spoilers on the Upper Surface of the Horizontal Stabilizer of a Model of a Radial-Engine Pursuit Airplane

Description: Report discussing an investigation into several types and sizes of flaps and spoilers located forward of the elevators on the upper surface of the horizontal stabilizer of a model of a radial-engine pursuit airplane. Information about the elevator characteristics, elevator-fixed and elevator-free balance lift coefficient, and trim drag coefficient for a range of Mach numbers is provided.
Date: January 21, 1946
Creator: Boddy, Lee E.
Partner: UNT Libraries Government Documents Department
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Aerodynamic Data for a Wing Section of the Republic XF-12 Airplane Equipped With a Double Slotted Flap

Description: Report presenting an investigation in the two-dimensional low-turbulence tunnels for the purpose of developing an optimum flap configuration for maximum lift on an airfoil section for the Republic XF-12 airplane equipped with a double slotted flap. Lift and flap loads were obtained at several flap deflections for two flap paths. Results regarding lift, drag, and flap loads are provided.
Date: January 1946
Creator: Cahill, Jones F.
Partner: UNT Libraries Government Documents Department
open access

An analysis of the skipping characteristics of some full-size flying boats

Description: From Introduction: "The purpose of this report is to gather together in one place information on the skipping characteristics of number of flying boats. A graph showing the influence of the hull form on the skipping characteristics is given which should be useful in laying out the proportions of the hull in preliminary design to insure good landing behavior."
Date: January 1946
Creator: Locke, F. W. S., Jr.
Partner: UNT Libraries Government Documents Department
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Correlation of Mixture Temperature Data Obtained From Bare Intake-Manifold Thermocouples

Description: "A relatively simple equation has been found to express with fair accuracy, variation in manifold-charge temperature with charge in engine operating conditions. This equation and associated curves have been checked by multi cylinder-engine data, both test stand and flight, over a wide range of operating conditions. Average mixture temperatures, predicted by the equations of this report, agree reasonably well with results within the same range of carburetor-air temperatures from laboratories and… more
Date: January 1946
Creator: White, H. Jack & Gammon, Goldie L.
Partner: UNT Libraries Government Documents Department
open access

Correlation Tests of the Ditching Behavior of an Army B-24D Airplane and a 1/16-Size Model

Description: Behaviors of both model and full-scale airplanes were ascertained by making visual observations, by recording time histories of decelerations, and by taking motion picture records of ditchings. Results are presented in form of sequence photographs and time-history curves for attitudes, vertical and horizontal displacements, and longitudinal decelerations. Time-history curves for attitudes and horizontal and vertical displacements for model and full-scale tests were in agreement; maximum longitu… more
Date: January 1946
Creator: Jarvis, George A. & Fisher, Lloyd J.
Partner: UNT Libraries Government Documents Department
open access

Determination of Gas Temperatures from the Frequency of Knock-Induced Gas Vibrations in an Internal-Combustion Engine

Description: Report of a study to develop a method of obtaining gas temperatures from the frequency of knock-induced gas vibrations in an internal-combustion engine cylinder. Temperatures calculated from frequency data were in agreement with temperatures measured by the spectral line-reversal method in previous investigations and were about 700 degrees Fahrenheit lower than temperatures obtained from thermodynamic charts.
Date: January 1946
Creator: Moeckel, W. E. & Evvard, J. C.
Partner: UNT Libraries Government Documents Department
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Ditching Tests of a 1/8-Scale Model of the Navy SB2c-1 Airplane (Army A-25) in Langley Tank Number 2 and on an Outdoor Catapult

Description: Report presenting testing to determine the best way to land the SB2C-1 airplane in calm and rough water and to determine its probable ditching performance. The behavior of the model was determined by making visual observations and by recording the maximum longitudinal decelerations and by taking motion pictures of the ditchings. Results regarding the effect of flaps, attitude, weight, a wing-low landing, effect of simulated damage, effect of tail wheel, ditching aids, and seaway are provided.
Date: January 1946
Creator: Jarvis, George A.
Partner: UNT Libraries Government Documents Department
open access

Effect of Compressibility on the Pressure and Forces Acting on a Modified NACA 65,3-019 Airfoil Having a 0.20-Chord Flap

Description: "An investigation has been conducted in the Langley rectangular high-speed tunnel to determine the effect of compressibility on the pressure distribution for a modified NACA 65,3-019 airfoil having a 0.20-chord flap. The investigation was made for an angle-of-attack range extending from -2 to 12 deg at .20 flap deflections from 0 to -12 deg. Test data were obtained for Mach numbers from 0.28 to approximately 0.74" (p. 1).
Date: January 1946
Creator: Lindsey, W. F.
Partner: UNT Libraries Government Documents Department
open access

Experimental Determination of the Effect of Negative Dihedral on Lateral Stability and Control Characteristics at High Lift Coefficients

Description: Report presenting the effects of negative dihedral on lateral stability and control characteristics at high lift coefficients determined by flight tests with a model. As the effective dihedral was decreased, the model became increasingly difficult to fly. Results regarding the effect of directional stability and lift coefficient on flight behavior are also provided.
Date: January 1946
Creator: McKinney, Marion O., Jr.
Partner: UNT Libraries Government Documents Department
open access

Free-Spinning, Longitudinal-Trim, and Tumbling Tests of 1/17.8-Scale Models of the Cornelius XFG-1 Glider

Description: Report discussing testing on the spin and recovery characteristics, longitudinal-trimming characteristics at extreme angles of attack, and tumbling characteristics of a model of the Cornelius XFG-1 glider. The effects of loading, mass distribution, and center-of-gravity position were determined. They also explored the inverted spin characteristics and spin-recovery parachute requirements.
Date: January 1946
Creator: Stone, Ralph W., Jr. & Daughtridge, Lee T., Jr.
Partner: UNT Libraries Government Documents Department
open access

Ground-Stand Cooling Investigation of an R-2600-22 Engine in a PBM-3D Nacelle

Description: Report discussing an investigation of the cooling characteristics of an R-2600-22 engine installed in a PBM-3D nacelle. The investigation explored the general cooling characteristics by the NACA cooling-correlation method and an investigation of specific points on the engine cylinder where cooling was critical, including the exhaust-valve-crown and number 3 cylinder.
Date: January 1946
Creator: Spencer, Robert C.; Petring, F. William & Prince, William R.
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Cowl-Flap and Cowl-Outlet Designs for the Boeing B-29 Power-Plant Installation

Description: Report discussing an investigation into cowl-flap and cowl-outlet designs for the B-29 in order to determine the effects of cowling performance of different types of flaps and elements of flaps. Details of the available pressure drop and cooling-air pressure-drop distribution are also provided.
Date: January 1946
Creator: Wyatt, DeMarquis D. & Conrad, E. William
Partner: UNT Libraries Government Documents Department
open access

An Investigation of Cowl Inlets for the B-29 Power-Plant Installation

Description: Report investigating five cowl-inlet configurations for the B-29 to obtain design information for improving the cowl performance. The effects of propeller spinners and increased inlet diameters on the cooling-air pressures at the cowl inlet and face of the engine and on the drag and critical speed of the cowl are described.
Date: January 1946
Creator: Monroe, Louis L. & Saari, Martin J.
Partner: UNT Libraries Government Documents Department
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Laboratory Investigation of Icing in the Carburetor and Supercharger Inlet Elbow of an Aircraft Engine 4: Effect of Throttle Design and Method of Throttle Operation on Induction-System Icing Characteristics

Description: "In order to eliminate the formation of ice on the carburetor throttle plates of an aircraft-engine induction system, two modifications of the throttle design and a variation in the method of throttle operation of the twin-barrel injection carburetor were tested" (p. 1). The modifications were investigated under severe icing conditions at normal power, maximum cruising power, and 60-percent normal power. The only modification that appeared to provide deicing assistance were the electrically hea… more
Date: January 1946
Creator: Chapman, G. E. & Zlotowski, E. E.
Partner: UNT Libraries Government Documents Department
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Laboratory Investigation of Icing in the Carburetor and Supercharger Inlet Elbow of an Aircraft Engine 6: Effect of Modifications to Fuel-Spray Nozzle on Icing Characteristics

Description: Report discussing modifications to the spray nozzle to prevent the formation of refrigeration icing in the induction system of an aircraft engine. Two fuel-injection systems, a spinner type and a drilled-inducer type, that prevent the formation of refrigerator icing satisfactorily were created.
Date: January 1946
Creator: Mulholland, Donald R. & Chapman, Gilbert E.
Partner: UNT Libraries Government Documents Department
open access

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
open access

Single-Cylinder Oil-Control Tests of Porous Chrome Plated Cylinder Barrels for Radial Air-Cooled Engines

Description: Report presenting a series of single-cylinder engine tests run to determine a satisfactory method of reducing oil consumption in radial air-cooled engines with flat-face compression rings as standard parts and equipped with cylinder barrels salvaged by porous chrome plating. Testing was conducted using porous chrome-plated cylinders with straight and choke bores with standard flat-face compression rings.
Date: January 1946
Creator: Johnson, Robert L. & Swikert, Max
Partner: UNT Libraries Government Documents Department
open access

Spray Characteristics of a Powered Dynamic Model of a Flying Boat Having a Hull With a Length-Beam Ratio of 9.0

Description: Report discusses an investigation into the spray characteristics of a twin-engine flying boat model similar to the Boeing XPBB-1 but with a modified length-beam ratio of the hull. The spray characteristics of the modified model compared favorably with the standard XPBB-1 flying boat and no adverse effects on spray characteristics were introduced by modifying the length-beam ratio and hull.
Date: January 1946
Creator: Olson, Roland E. & Bell, Joe W.
Partner: UNT Libraries Government Documents Department
open access

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
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Wind-Tunnel Investigation of an NACA 66-Series 16-Percent-Thick Low-Drag Tapered Wing With Fowler and Split Flaps

Description: Report presenting testing to determine the aerodynamic characteristics of an NACA 66-series 16-percent-thick low-drag tapered wing with Fowler and split flaps. The wing had a straight trialing edge and a constant-chord center section. Results regarding lift and pitching-moment characteristics and stalling characteristics are provided.
Date: January 1946
Creator: Neely, Robert H. & Foster, Gerald V.
Partner: UNT Libraries Government Documents Department
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Measurement of Individual Aileron Hinge Moments and Aileron Control Characteristics of a P-40F Airplane

Description: "Flight measurements have been made of the individual aileron hinge moments, aileron rolling effectiveness pb/2V ,and stick-force characteristics in abrupt aileron rolls with a P-40F airplane (AAF No. 41-14119) over an indicated airspeed range from 108 to 304 miles per hour. Three methods for measuring the rate of change of hinge moment with angle of attack were investigated. Presented for comparison with the flight results are data from two-dimensional wind-tunnel tests of the wing-aileron pro… more
Date: January 29, 1945
Creator: Goranson, R. Fabian
Partner: UNT Libraries Government Documents Department
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Langley Full-Scale-Tunnel Stability and Control Tests of the Bell YP-59A Airplane

Description: Report discussing tests of the drag clean-up and stability of the Bell YP-59A jet-propelled airplane. The general stability, static stability, and control characteristics were examined. Specific details are also included about the effects of the exhaust jet on air flow at the tail.
Date: January 18, 1945
Creator: Brewer, Gerald W.
Partner: UNT Libraries Government Documents Department
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The Influence of Exhaust Pressure on Knock-Limited Performance

Description: Report discussing testing on two types of single cylinders to determine the effect of the relation of exhaust pressure to inlet-air pressure on knock-limited performance. Variables explored included exhaust pressure, fuel-air ratio, and engine speed. Three types of fuels were also used to explore the effect of exhaust pressure on fuel ratings.
Date: January 5, 1945
Creator: Cook, Harvey A.; Held, Louis F. & Pritchard, Ernest I.
Partner: UNT Libraries Government Documents Department
open access

Measurement of Flying Qualities of a Douglas A-26B Airplane (AAF No. 41-39120) 2: Lateral and Directional Stability and Control Characteristics

Description: Report discussing testing of the Douglas A-26B to determine the lateral and directional stability and control characteristics. Information about the control-free lateral and directional oscillations, sideslip due to full aileron deflection, control-fixed and control-free directional stability, effective dihedral, side force due to sideslip, rudder control characteristics, variation of rudder and aileron force with speed, and response to abrupt aileron deflection are described.
Date: January 4, 1945
Creator: Sjoberg, S. A.; Crane, H. L. & Hoover, H. H.
Partner: UNT Libraries Government Documents Department
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