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Single-cylinder oil-control tests of porous chrome plated cylinder barrels for radial air-cooled engines
No Description Available.
Effect of the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger for thermal ice prevention
No Description Available.
An investigation of a thermal ice-prevention system for a C-46 cargo airplane V : effect of thermal system on airplane cruise performance
No Description Available.
Wind-tunnel investigation of the effects of spoilers on the characteristics of a low-drag airfoil equipped with a 0.25-chord slotted flap
No Description Available.
Tests of a thermal ice-prevention system for a wing leading-edge landing-light installation
No Description Available.
The effect of high-resistance ignition cable on the erosion of spark-plug electrodes
No Description Available.
A cooling correlation equation for a double-row radial engine based on the temperature of the exhaust-valve seat
No Description Available.
Cooling of a double-row radial engine by water injection to the individual cylinders
No Description Available.
The effect of increase in combustion-air inlet temperature from 80 to 130 F on the sea-level performance of a 22-inch-diameter pulse-jet engine
No Description Available.
Correlation of mixture temperature data obtained from bare intake-manifold thermocouples
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 test stands other than the NACA.
The effect of compression ratio on knock limits of high-performance fuels in a CFR engine I : blends of triptane and 28-R fuel
No Description Available.
The Effect of Compression Ratio on Knock Limits of High-Performance Fuels in a CFR Engine II : Blends of 2,2,3-Trimethylpentane with 28-R
The knock-limited performance of blends of 0,50; and 100 percent by volume of 2,2,3-trimethylpentane in 28-R fuel determined with a modified F-4 engine at three sets of conditions varying from severe to mild at each of three compression ratios (6.0, 8.0, and 10.0). A comparison of the knock-limited performance of 2,2,3-trimethylpentane with that of triptane (2,2,3-trimethylbutane) is included. The knock-Limited performance of 2,2,3-trimethylpontane was usually more sensitive to either compression ratio or inlet-air temperature than 28-R fuel, but the ratio of the knock-limited indicated mean effective pressure of a given blend containing 2,2,3-trimethypentane and 28-R to the indicated mean effective pressure of 28-R alone was not greatly affected by compression ratio if the engine operating conditions were mild. Although 2,2,3-trimethylpentane in general had a lower knock-limited performance than triptane, the characteristics of the two fuels were somewhat similar.
Effect of engine-operating variables and internal coolants on spark-advance requirements of a liquid-cooled cylinder
No Description Available.
The effect of ethylene dibromide on the knock-limited performance of leaded and nonleaded S reference fuel
No Description Available.
The effect of compression ratio on knock limits of high-performance fuels in a CFR engine III : blends of 2,3-dimethylpentane with 28-R
No Description Available.
Effect of internal coolants on the knock-limited performance of an Allison V-1710-99 engine with a compression ratio of 6.0
No Description Available.
Efficiency of a radial-flow exhaust-gas turbosupercharger turbine with a 12.75-inch tip diameter
No Description Available.
Effect of fuel volatility and mixture temperature on the knocking characteristics of a liquid-cooled single-cylinder test engine
No Description Available.
Correlation of the Characteristics of Single-Cylinder and Flight Engines in Tests of High-Performance Fuels in an Air-Cooled Engine I : Cooling Characteristics
Variable charge-air flow, cooling-air pressure drop, and fuel-air ration investigations were conducted to determine the cooling characteristics of a full-scale air-cooled single cylinder on a CUE setup. The data are compared with similar data that were available for the same model multicylinder engine tested in flight in a four-engine airplane. The cylinder-head cooling correlations were the same for both the single-cylinder and the flight engine. The cooling correlations for the barrels differed slightly in that the barrel of the single-cylinder engine runs cooler than the barrel of te flight engine for the same head temperatures and engine conditions.
Correlation of the characteristics of single-cylinder and flight engines in tests of high-performance fuels in an air-cooled engine II : knock-limited charge-air flow and cylinder temperatures
An investigation was conducted to correlate the knock limited performance of flight and single-cylinder engines under a variety of operating conditions.
Determination of air-consumption parameters for two radial aircraft engines
No Description Available.
Wind-tunnel tests of the 0.15-scale powered model of the Fleetwing XBTK-1 airplane : lateral stability and control
No Description Available.
Wind-Tunnel Tests of the 0.15-Scale Powered Model of the Fleetwings XBTK-1 Airplane : Longitudinal Stability and Control
An investigation was made of the static longitudinal stability, and control and stall characteristics of XBTK-1 dive bomber. Results indicate that the longitudinal stability will probably be satisfactory for all contemplated flight conditions at the rear-most CG location with elevator both fixed and free. Power effects were small. Sufficient elevator control will be available to trim in any flight condition above the ground. Increasing the slotted flap deflection above 30 degrees only slightly increased the max. lift coefficient.
Two-dimensional wind-tunnel investigation of 0.20-airfoil-chord plain ailerons of different contour on an NACA 65(sub 1)-210 airfoil section
No Description Available.
Lift tests of a 0.1536c thick Douglas airfoil section of NACA 7-series type equipped with a lateral-control device for use with a full-span double-slotted flap on the C-74 airplane
No Description Available.
An estimate of the effect of engine supercharging on the take-off thrust of a typical helicopter at different altitudes and temperatures
No Description Available.
An Experimental Investigation of Flow Conditions in the Vicinity of an NACA D(Sub S)-Type Cowling
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.
Free-spinning, longitudinal-trim, and tumbling tests of 1/17.8-scale models of the Cornelius XFG-1 glider
No Description Available.
Langley full-scale-tunnel stability and control tests of the Bell YP-59A airplane
No Description Available.
Two-dimensional wind-tunnel investigation of six airfoil sections for the wing of the Vega XP2V-1 airplane
No Description Available.
Two-dimensional wind-tunnel investigation of spoiler aileron flap model for the Hughes XF-11 airplane
No Description Available.
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
No Description Available.
Wind-tunnel investigation of alternative propellers operating behind deflected wing flaps for the XB-36 airplane
No Description Available.
Vibration-response tests of a 1/5-scale model of the Grumman F6F airplane in the Langley 16-foot high-speed tunnel
No Description Available.
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
No Description Available.
Tests of a 1/14-scale powered model of the XB-36 airplane in the Langley 19-foot pressure tunnel I : stalling characteristics and aileron effectiveness of several wing and flap arrangements
No Description Available.
Tests of a 1/7-scale powered model of the Kaiser tailless airplane in the Langley full-scale tunnel
No Description Available.
Flight tests of a rudder with a spring tab on an F6F-3 airplane (BuAer No.04776)
No Description Available.
Flight tests of an SB2C-3 airplane with a production and tilted propeller axis
No Description Available.
Test of 0.14-scale models of the control surfaces of Army project MX-511 in attitudes simulating spins
No Description Available.
Wind-Tunnel Tests of a 1/5-Scale Semispan Model of the Republic XF-12 Horizontal Tail Surface
Wind-tunnel tests of a 1/5-scale semispan model of the Republic XF-12 horizontal tail surface equipped with an internally balanced elevator were conducted in the 6- by 6-foot test section of the Langley stability tunnel. The tests included measurements of the aerodynamic characteristics of the horizontal tail with and without a beveled trailing edge and also included measurements of the tab characteristics. The variation of the aerodynamic characteristics with boundary-layer conditions and leakage in the internal-balance chambers, measurements of the boundary-layer displacement thickness near the elevator hinge axis, and pressure distributions at the mean geometric chord were also obtained. The results showed that the hinge-moment characteristics of the elevator were critical to boundary-layer conditions and internal-balance leakage. Increasing the boundary-layer displacement thickness by use of roughness strips reduced the rate of change of elevator hinge moments with tab deflection by about 20 percent. The present horizontal tail appears to be unsatisfactory for longitudinal stability with power on, however, an increase in horizontal-tail lift effectiveness should correct this difficulty. The maneuvering stick force per unit acceleration will be extremely critical to minor variations of the elevator hinge moments if the elevator is linked directly to the stick.
Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail Incorporating a De-Icing Air Duct
A 1/6-scale model of the Republic XF-12 vertical tail with stub fuselage, stub horizontal tail, and a de-icing air duct was tested in the Langley stability tunnel. The investigation consisted of a study of the effects of the duct, with and without air flow, on the aerodynamic characteristics of the model. The model tested was a revision of a model previously tested in the Langley stability tunnel. The revised model differed from the original model in that it incorporated a de-icing air duct, included a dorsal fin, and had a larger stub fuselage. A comparison of data obtained form tests of the original and revised models was made. The results of the investigation indicated that the air duct had very little effect on the aerodynamic characteristics of the model. A small change occurred in the variation of rudder hinge-moment coefficient with angle of attack but it is believed that this change can be corrected by a properly applied spring tab.
Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail with Stub Fuselage and Stub Horizontal Tail
A 1/6-scale model of the Republic XF-12 vertical tail with stub fuselage and stub horizontal tail was tested in the Langley stability tunnel to determine the aerodynamic characteristics of the model, The investigation included a study of the effects of boundarylayer thickness, rudder area, and cover-plate alinement on the aerodynamic characteristics. Tuft studies were made in the vicinity of the junction of the vertical and stub horizontal tails. The results of the investigation indicated that the flow in the vicinity of the junction of the vertical and stub horizontal tails was only slightly improved by the addition of a fillet. An increase in boundary-layer thickness produced a slight decrease in rudder effectiveness. The increase in lift of the combined rudders over that of the upper rudder alone was not proportional at low deflections and was approximately proportional at high deflections to the increase in rudder area. When the balance-chamber cover plates were bowed out, the change in rudder hinge moment with rudder angle was less negative. The variation of the lift coefficient with angle of attack and the variation, at small values of angle of attack, of rudder hinge-noment coefficient with angle of attack was approximately the same for all model configurations tested. The upper rudder used in conjunction with a tab was found to satisfy the Army specifications regarding asymmetric power on a multiengine airplane.
Wind-Tunnel Tests of a Portion of a PV-2 Helicopter Rotor Blade
A portion of a PV-2 helicopter rotor blade has been tested in the 6- by 6-foot test section of the Langley stability tunnel to determine if the aerodynamic characteristics were seriously affected by cross flow or fabric distortion. The outer portion of the blade was tested as a reflection plane model pivoted about the tunnel wall to obtain various angles of cross flow over the blade. Because the tunnel wall acts as a plane of sy~try, the measured aerodynamic characteristics correspond to those of an airfoil having various angles of sweepforward and sweepback. Tests were made with the vents on the lower surface open and also with the vents sealed and the internal pressure held at -20 inches of water producing an internal pressure coefficient of -1.059. The change in contour resulting from the range of internal pressures used had very little effect on the aerodynamic characteristics of the blade. The test methods were considered to simulate inadequately the flow conditions over the rotor blade because the effects of cross flow were limited to conditions corresponding to sweep of the blade. The results indicated that this type of cross flow had only minor effects on the aerodynamic characteristics of the blade. It is believed, therefore, that future tests to determine the effects on the aerodynamic characteristics of cross flow should utilize complete rotors.
Full-scale-tunnel performance tests of the PV-2 helicopter rotor
No Description Available.
Correlation Tests of the Ditching Behavior of an Army B-24D Airplane and a 1/16-Size Model
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 longitudinal decelerations for both ditchings did not occur at same part of run; full-scale maximum deceleration was 50 percent greater.
Flight investigation of modifications to improve the elevator control-force characteristics of the Curtiss SB2C-10 airplane in maneuvers
No Description Available.
Flight investigation of factors affecting the carburetor ram and nacelle drag of an A-26B airplane
No Description Available.
A method for correlating the cooling data of liquid-cooled engines and its application to the Allison V-3420-11 engine
No Description Available.
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
No Description Available.