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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Memorandum Report
 Collection: National Advisory Committee for Aeronautics Collection
Wind-Tunnel Investigation of Devices for Improving the Diving Characteristics of Airplanes
No Description digital.library.unt.edu/ark:/67531/metadc61223/
Measurements of the flying qualities of a Bell P-39D-1 airplane (AAF NO. 41-28378)
No Description digital.library.unt.edu/ark:/67531/metadc61077/
Resume of NACA stability and control tests of the Bell P-63 series airplane
No Description digital.library.unt.edu/ark:/67531/metadc61079/
Bending and shear stresses developed by the instantaneous arrest of the root of a cantilever beam with a mass at its tip
No Description digital.library.unt.edu/ark:/67531/metadc62215/
Estimates of the vertical-tail loads of a Bell P-63A-1 airplane (AAF No. 42-68889) in accelerated rolling maneuvers based on flight tests with two vertical-tail arrangements
No Description digital.library.unt.edu/ark:/67531/metadc61501/
F-3 and F-4 engine tests of several high-antiknock components of aviation fuel
No Description digital.library.unt.edu/ark:/67531/metadc62363/
An investigation of the mutual interference effects of a tail-surface : stern propeller installation on a model simulating the Douglas XB-42 empennage
No Description digital.library.unt.edu/ark:/67531/metadc61575/
The low-temperature solubility of 24 aromatic amines in aviation gasoline
No Description digital.library.unt.edu/ark:/67531/metadc62286/
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/
Flying qualities of a high-speed bomber with a dual pusher propeller aft of the empennage as estimated from wind-tunnel tests of a 1/8-scale powered model
No Description digital.library.unt.edu/ark:/67531/metadc61057/
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/
Charts showing stability and control characteristics of airplanes in flight
No Description digital.library.unt.edu/ark:/67531/metadc60953/
Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines I : determination of cooling characteristics of flight engine
No Description digital.library.unt.edu/ark:/67531/metadc62522/
Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines II : flight knock data and comparison of fuel knock limits with engine cooling limits in flight
No Description digital.library.unt.edu/ark:/67531/metadc62523/
Flight variables affecting fuel-vapor loss from a fuel tank
No Description digital.library.unt.edu/ark:/67531/metadc62282/
Knock-limited performance of blends of AN-F-28 fuel containing 2 percent aromatic amines IV
No Description digital.library.unt.edu/ark:/67531/metadc62352/
Measurement of flying qualities of a Douglas A-26B airplane (AAF No. 41-39120) I : longitudinal stability and control characteristics
No Description digital.library.unt.edu/ark:/67531/metadc61050/
Tests of a thermal ice-prevention system for a wing leading-edge landing-light installation
No Description digital.library.unt.edu/ark:/67531/metadc279556/
Power-off tests of the Northrop N9M-2 tailless airplane in the 40- by 80-foot wind tunnel
No Description digital.library.unt.edu/ark:/67531/metadc53585/
Flight tests of the high-speed performance of a P-51B airplane (AAF no. 43-12105)
No Description digital.library.unt.edu/ark:/67531/metadc53365/
High-speed wind-tunnel tests of semispan horizontal tails with fabric-covered and metal-covered elevators for a bomber airplane
No Description digital.library.unt.edu/ark:/67531/metadc61573/
Wind Tunnel Investigation of the Effects of Slot Shape and Flap Location on the Characteristics of a Low-Drag Airfoil Equipped with a 0.25-Chord Slotted Flap
Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment measurements throughout useful angle of attack range for constant flap deflection and position of a low-drag airfoil. Two slots were investigated and practical flap paths were selected for each Slot shape had a negligible effect on the maximum lift coefficient flap deflected, the rounded-entry slot had lower profile drag. digital.library.unt.edu/ark:/67531/metadc61426/
Correlation of engine-cooling data
No Description digital.library.unt.edu/ark:/67531/metadc61958/
Langley full-scale-tunnel stability and control tests of the Bell YP-59A airplane
No Description digital.library.unt.edu/ark:/67531/metadc60863/
Measurement of flying qualities of a Douglas A-26B airplane (AAF No. 41-39120) II : lateral and directional stability and control characteristics
No Description digital.library.unt.edu/ark:/67531/metadc61054/
Measurement of flying qualities of a Douglas A-26B airplane (AAF No. 41-39120) III : stalling characteristics
No Description digital.library.unt.edu/ark:/67531/metadc61055/
Measurement of individual aileron hinge moments and aileron control characteristics of a P-40F airplane
No Description digital.library.unt.edu/ark:/67531/metadc61642/
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/
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/
Cooling of a double-row radial engine by water injection to the individual cylinders
No Description digital.library.unt.edu/ark:/67531/metadc62015/
Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) I : longitudinal stability and control
No Description digital.library.unt.edu/ark:/67531/metadc61068/
Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) II : lateral and directional stability and control
No Description digital.library.unt.edu/ark:/67531/metadc61071/
Flight measurements of the flying qualities of an F6F-3 airplane (BuAer No. 04776) III : stalling characteristics
No Description digital.library.unt.edu/ark:/67531/metadc61072/
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/
Knock-limited blending characteristics of benzene, toluene, mixed xylenes, and cumene in an air-cooled cylinder
No Description digital.library.unt.edu/ark:/67531/metadc62289/
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/
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/
Characteristics of several single- and dual-rotating propellers in negative thrust
No Description digital.library.unt.edu/ark:/67531/metadc62187/
The effect of modified baffles and auxiliary-cooling ducts on the cooling of a double-row radial engine
No Description digital.library.unt.edu/ark:/67531/metadc62016/
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/
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 the Sikorsky HNS-1 (Army YR-4B) helicopter I : experimental data on level-flight performance with original rotor blades
No Description digital.library.unt.edu/ark:/67531/metadc61836/
High-speed photographs of a YR-4B production rotor blade for simulated flight conditions in the Langley full-scale tunnel
No Description digital.library.unt.edu/ark:/67531/metadc61844/
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/
Investigation of slipstream effects on a wing-inlet oil-cooler ducting system of a twin-engine airplane in the Ames 40- by 80-foot wind tunnel
No Description digital.library.unt.edu/ark:/67531/metadc62473/
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. digital.library.unt.edu/ark:/67531/metadc65602/
Characteristics of the BMW 801D2 automatic engine control as determined from bench tests
No Description digital.library.unt.edu/ark:/67531/metadc62109/
Comparison of predicted and actual control-fixed stability and control characteristics of a Douglas A-26B airplane
No Description digital.library.unt.edu/ark:/67531/metadc61056/
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