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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Memorandum Report
Single-cylinder oil-control tests of porous chrome plated cylinder barrels for radial air-cooled engines
No Description digital.library.unt.edu/ark:/67531/metadc279560/
Effect of the performance of a turbosupercharged engine of an exhaust-gas-to-air heat exchanger for thermal ice prevention
No Description digital.library.unt.edu/ark:/67531/metadc279594/
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 digital.library.unt.edu/ark:/67531/metadc279663/
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 digital.library.unt.edu/ark:/67531/metadc279657/
Tests of a thermal ice-prevention system for a wing leading-edge landing-light installation
No Description digital.library.unt.edu/ark:/67531/metadc279556/
Characteristics of the BMW 801D2 automatic engine control as determined from bench tests
No Description digital.library.unt.edu/ark:/67531/metadc62109/
The effect of high-resistance ignition cable on the erosion of spark-plug electrodes
No Description digital.library.unt.edu/ark:/67531/metadc62091/
A cooling correlation equation for a double-row radial engine based on the temperature of the exhaust-valve seat
No Description digital.library.unt.edu/ark:/67531/metadc62018/
Cooling of a double-row radial engine by water injection to the individual cylinders
No Description digital.library.unt.edu/ark:/67531/metadc62015/
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 digital.library.unt.edu/ark:/67531/metadc62549/
Control of cylinder temperatures by thermostatically operated internal-coolant valves
No Description digital.library.unt.edu/ark:/67531/metadc61968/
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. digital.library.unt.edu/ark:/67531/metadc61878/
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 digital.library.unt.edu/ark:/67531/metadc62519/
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. digital.library.unt.edu/ark:/67531/metadc62525/
Effect of engine-operating variables and internal coolants on spark-advance requirements of a liquid-cooled cylinder
No Description digital.library.unt.edu/ark:/67531/metadc61914/
The effect of ethylene dibromide on the knock-limited performance of leaded and nonleaded S reference fuel
No Description digital.library.unt.edu/ark:/67531/metadc62310/
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 digital.library.unt.edu/ark:/67531/metadc62381/
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 digital.library.unt.edu/ark:/67531/metadc61974/
Efficiency of a radial-flow exhaust-gas turbosupercharger turbine with a 12.75-inch tip diameter
No Description digital.library.unt.edu/ark:/67531/metadc61860/
Effect of fuel volatility and mixture temperature on the knocking characteristics of a liquid-cooled single-cylinder test engine
No Description digital.library.unt.edu/ark:/67531/metadc62535/
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. digital.library.unt.edu/ark:/67531/metadc62546/
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. digital.library.unt.edu/ark:/67531/metadc62547/
Determination of air-consumption parameters for two radial aircraft engines
No Description digital.library.unt.edu/ark:/67531/metadc61869/
Wind-tunnel tests of the 0.15-scale powered model of the Fleetwing XBTK-1 airplane : lateral stability and control
No Description digital.library.unt.edu/ark:/67531/metadc62649/
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. digital.library.unt.edu/ark:/67531/metadc62647/
Comparison of the knock-limited performance of triptane with 23 other purified hydrocarbons
No Description digital.library.unt.edu/ark:/67531/metadc62298/
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 digital.library.unt.edu/ark:/67531/metadc61394/
Calculation of the aileron and elevator stick forces and rudder pedal forces for the Bell XP-83 airplane (project MX-511) in spins
No Description digital.library.unt.edu/ark:/67531/metadc61570/
Calibrations of service pitot tubes in the Langley 24-inch high-speed tunnel
No Description digital.library.unt.edu/ark:/67531/metadc62408/
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 digital.library.unt.edu/ark:/67531/metadc61291/
Analysis and correlation of data obtained by six laboratories on fuel-vapor loss from fuel tanks during simulated flight
No Description digital.library.unt.edu/ark:/67531/metadc62280/
Attainment of a straight-line trajectory for a preset guided missile with special reference to effect of wind or target motion
No Description digital.library.unt.edu/ark:/67531/metadc62433/
Charts showing stability and control characteristics of airplanes in flight
No Description digital.library.unt.edu/ark:/67531/metadc60953/
An estimate of the effect of engine supercharging on the take-off thrust of a typical helicopter at different altitudes and temperatures
No Description digital.library.unt.edu/ark:/67531/metadc61867/
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. digital.library.unt.edu/ark:/67531/metadc62102/
Free-spinning, longitudinal-trim, and tumbling tests of 1/17.8-scale models of the Cornelius XFG-1 glider
No Description digital.library.unt.edu/ark:/67531/metadc60856/
Langley full-scale-tunnel stability and control tests of the Bell YP-59A airplane
No Description digital.library.unt.edu/ark:/67531/metadc60863/
Two-dimensional wind-tunnel investigation of six airfoil sections for the wing of the Vega XP2V-1 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61361/
Two-dimensional wind-tunnel investigation of spoiler aileron flap model for the Hughes XF-11 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61641/
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 digital.library.unt.edu/ark:/67531/metadc61393/
Wind-tunnel investigation of alternative propellers operating behind deflected wing flaps for the XB-36 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61191/
Vibration-response tests of a 1/5-scale model of the Grumman F6F airplane in the Langley 16-foot high-speed tunnel
No Description digital.library.unt.edu/ark:/67531/metadc60875/
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 digital.library.unt.edu/ark:/67531/metadc61791/
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 digital.library.unt.edu/ark:/67531/metadc61189/
Tests of a 1/7-scale powered model of the Kaiser tailless airplane in the Langley full-scale tunnel
No Description digital.library.unt.edu/ark:/67531/metadc61218/
Flight tests of a rudder with a spring tab on an F6F-3 airplane (BuAer No.04776)
No Description digital.library.unt.edu/ark:/67531/metadc61590/
Flight tests of an SB2C-3 airplane with a production and tilted propeller axis
No Description digital.library.unt.edu/ark:/67531/metadc61047/
Test of 0.14-scale models of the control surfaces of Army project MX-511 in attitudes simulating spins
No Description digital.library.unt.edu/ark:/67531/metadc61569/
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. digital.library.unt.edu/ark:/67531/metadc64935/
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. digital.library.unt.edu/ark:/67531/metadc64934/
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