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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Wartime Reports
 Collection: Technical Report Archive and Image Library
Acceleration, stress, and deflection measurements on the XB-15 bomber in gusty air
No Description digital.library.unt.edu/ark:/67531/metadc61098/
Accelerations and bottom pressures measured on a B-24D airplane in a ditching test
No Description digital.library.unt.edu/ark:/67531/metadc61135/
Accelerations measured at center of gravity and along span of the wing of a B-24D airplane in landing impacts
No Description digital.library.unt.edu/ark:/67531/metadc61134/
Addition of heat to a compressible fluid in motion
No Description digital.library.unt.edu/ark:/67531/metadc62512/
Additional design charts relating to the stalling of tapered wings
No Description digital.library.unt.edu/ark:/67531/metadc61269/
An additional investigation of the high-speed lateral-control characteristics of spoilers
No Description digital.library.unt.edu/ark:/67531/metadc60955/
Additional power-on wind-tunnel tests of the 1/8-scale model of the Brewster F2A airplane with full-span slotted flaps
No Description digital.library.unt.edu/ark:/67531/metadc62635/
Adjustment of stick force by a nonlinear aileron-stick linkage
No Description digital.library.unt.edu/ark:/67531/metadc61609/
The advantages of uniform fuel distribution for air-cooled engines from considerations of cooling requirements and fuel economy
No Description digital.library.unt.edu/ark:/67531/metadc61935/
Aerodynamic and hydrodynamic tests of a family of models of flying-boat hulls derived from a streamline body : NACA model 84 series
No Description digital.library.unt.edu/ark:/67531/metadc61711/
Aerodynamic characteristics and flap loads of perforated double split flaps on a rectangular NACA 23012 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61464/
Aerodynamic characteristics and flap loads of the brake-flap installation on the 0.40-scale model of the F4F-3 left wing panel
No Description digital.library.unt.edu/ark:/67531/metadc61360/
Aerodynamic characteristics for internal-balance and Frise type ailerons on an NACA 6 series low-drag tip section of the wing for the XP-63 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61354/
Aerodynamic characteristics of a 1/8-scale powered model of a high-speed bomber with a dual pusher propeller aft of the empennage
No Description digital.library.unt.edu/ark:/67531/metadc61201/
Aerodynamic characteristics of a 4-engine monoplane showing comparison of air-cooled and liquid-cooled engine installations
No Description digital.library.unt.edu/ark:/67531/metadc62601/
Aerodynamic characteristics of a 4-engine monoplane showing effects of enclosing the engines in the wing and comparisons of tractor- and pusher-propeller arrangements
No Description digital.library.unt.edu/ark:/67531/metadc62602/
Aerodynamic characteristics of a slot-lip aileron and slotted flap for dive brakes
No Description digital.library.unt.edu/ark:/67531/metadc61438/
Aerodynamic characteristics of four NACA airfoil sections designed for helicopter rotor blades
No Description digital.library.unt.edu/ark:/67531/metadc61378/
Aerodynamic characteristics of several modifications of a 0.45-scale model of the vertical tail of the Curtiss XP-62 airplane
No Description digital.library.unt.edu/ark:/67531/metadc62683/
Aerodynamic characteristics of the NACA 747A315 and 747A415 airfoils from tests in the NACA two-dimensional low-turbulence pressure tunnel
No Description digital.library.unt.edu/ark:/67531/metadc61427/
Aerodynamic data for a wing section of the Republic XF-12 airplane equipped with a double slotted flap
No Description digital.library.unt.edu/ark:/67531/metadc61451/
Aerodynamic factors affecting the ability of a pilot to return an airplane to level from a banked attitude by use of the rudder alone and without change of heading
No Description digital.library.unt.edu/ark:/67531/metadc61018/
Aerodynamic problems in the design of efficient propellers
No Description digital.library.unt.edu/ark:/67531/metadc62127/
Aerodynamic tests of a full-scale TBF-1 aileron installation in the Langley 16-foot high-speed tunnel
The failure of wing panels on a number of TBF-1 and TBM-1 airplanes in flight has prompted several investigations of the possible causes of failure. 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. The tests were made of a 12-foot-span section including the tip and aileron of the right wing of a TBF-1 airplane. Hinge moments, control-link stresses due to aerodynamic buffeting, and fabric-deflection photographs were obtained at true airspeeds ranging from 110 to 365 miles per hour. The aileron hinge-moment coefficients were found to vary only slightly with airspeed in spite of the large fabric deflections that developed as the speed was increased. An analysis of these results indicated that the resultant hinge moment of the ailerons as installed in the airplane would tend to restore the ailerons to their neutral position for all the high-speed flight conditions covered in the tests. Serious aerodynamic buffeting occurred at up aileron angles of -10 degrees or greater because of stalling of the sharp projecting lip of the Frise aileron. The peak stresses set up in the aileron control linkages in the buffeting condition were as high as three times the mean stress. During the hinge-moment investigation, flutter of the test installation occurred at airspeeds of about 150 miles per hour. This flutter condition was investigated in some detail and slow-motion pictures were made of the motion of the wing tip and aileron. The flutter was found to involve simultaneous normal bending and chordwise oscillation of the wing and flapping of the aileron. The aileron motion appeared to be coupled with this flutter condition and was investigated in some detail and slow-motion pictures were made of the motion of the wing tip and aileron. The flutter was found to involve simultaneous normal bending and chordwise oscillation of the wing and flapping of the aileron. The aileron motion appeared to be coupled with the motion of the wing through the mass unbalance of the aileron in the normal-to-chord plane due to location of the hinge line 2.17 inches below the center of gravity of the aileron. Flutter did not occur when the installation was stiffened to prevent chordwise motion or when the bending frequency of the aileron system was appreciably higher than that of the wing as in the complete airplane installation. digital.library.unt.edu/ark:/67531/metadc65423/
Aerodynamic tests of an AN-M-65-AEON 1000-pound radio-controlled bomb in the LMAL 16-foot high-speed tunnel
No Description digital.library.unt.edu/ark:/67531/metadc62572/
Aerodynamic tests of an M-31 bomb in the 8-foot high-speed tunnel
No Description digital.library.unt.edu/ark:/67531/metadc62440/
Aerodynamic tests of an NACA 66(215)-116, a=0.6 airfoil with a 0.25c slotted flap for the Fleetwings XA-39 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61411/
The aerodynamic tests of three Edo floats for the SB2U-3, 0S2U-2, and XSB2C-2 seaplanes - NACA models 106-K, 107-K, and 125-AH
No Description digital.library.unt.edu/ark:/67531/metadc61712/
Aerodynamics of the carburetor air scoop and the engine cowling of a single-engine torpedo-bomber-type airplane
No Description digital.library.unt.edu/ark:/67531/metadc62050/
Air-consumption parameters for automatic mixture control of aircraft engines
No Description digital.library.unt.edu/ark:/67531/metadc279682/
Air-flow and performance characteristics of engine-stage supercharger of a double-row radial aircraft engine II : effect of design variables
No Description digital.library.unt.edu/ark:/67531/metadc62038/
Air-flow and performance characteristics of the engine-stage supercharger of a double-row radial aircraft engine I : effect of operating variables
No Description digital.library.unt.edu/ark:/67531/metadc62036/
Air-flow surveys in the region of the tail surfaces of a single-engine airplane equipped with dual-rotating propellers
No Description digital.library.unt.edu/ark:/67531/metadc61168/
Airfoil-contour modifications based on (epsilon)-curve method of calculating pressure distribution
No Description digital.library.unt.edu/ark:/67531/metadc61280/
Airfoil section data from tests of 10 practical- construction sections of helicopter rotor blades submitted by the Sikorsky Aircraft Division, United Aircraft Corporation
No Description digital.library.unt.edu/ark:/67531/metadc61461/
Airspeed fluctuations as a measure of atmospheric turbulence
No Description digital.library.unt.edu/ark:/67531/metadc61123/
Altitude rating of electrical apparatus
No Description digital.library.unt.edu/ark:/67531/metadc62410/
Altitude-wind-tunnel tests of power-plant installation in jet-propelled fighter
No Description digital.library.unt.edu/ark:/67531/metadc61183/
Aluminum-zinc-magnesium-copper casting alloys
No Description digital.library.unt.edu/ark:/67531/metadc62227/
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/
Analysis of a thermal ice-prevention system for wing leading-edge landing-light installations
No Description digital.library.unt.edu/ark:/67531/metadc62479/
Analysis of available data on control surfaces having plain-overhang and Frise balances
No Description digital.library.unt.edu/ark:/67531/metadc61487/
Analysis of available data on the effectiveness of ailerons without exposed overhang balance
No Description digital.library.unt.edu/ark:/67531/metadc61635/
Analysis of Effect of Rolling Pull-Outs on Wing and Aileron Loads of a Fighter Airplane
An analysis was made to determine the effect of rolling pull-out maneuvers on the wing and aileron loads of a typical fighter airplane, the P-47B. The results obtained indicate that higher loads are imposed upon wings and ailerons because of the rolling pull-out maneuver, than would be obtained by application of the loading requirements to which the airplane was designed. An increase of 102 lb or 15 percent of wing weight would be required if the wing were designed for rolling pull-out maneuver. It was also determined that the requirements by which the aileron was originally designed were inadequate. digital.library.unt.edu/ark:/67531/metadc61279/
Analysis of factors affecting net lift increment attainable with trailing-edge split flaps on tailless airplanes
No Description digital.library.unt.edu/ark:/67531/metadc61281/
Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system
No Description digital.library.unt.edu/ark:/67531/metadc279610/
An analysis of jet-propulsion systems making direct use of the working substance of a thermodynamic cycle
No Description digital.library.unt.edu/ark:/67531/metadc62462/
An analysis of life expectancy of airplane wings in normal cruising flight
No Description digital.library.unt.edu/ark:/67531/metadc62527/
The analysis of strains indicated by multiple-strand resistance-type wire strain gages used as rosettes
No Description digital.library.unt.edu/ark:/67531/metadc62612/
An analysis of the effect of core structure and performance on volume and shape of cross-flow tubular intercoolers
No Description digital.library.unt.edu/ark:/67531/metadc62073/
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