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  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Wartime Reports
 Collection: Technical Report Archive and Image Library
Lift and drag data for 30 pusher-propeller shaft housings on an NACA 65,3-018 airfoil section
No Description digital.library.unt.edu/ark:/67531/metadc61406/
Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61351/
Lift and drag characteristics of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation
No Description digital.library.unt.edu/ark:/67531/metadc61359/
Pressure-distribution measurements of a low-drag airfoil with slotted flap submitted by Curtiss-Wright Corporation
No Description digital.library.unt.edu/ark:/67531/metadc61482/
Interference effects of longitudinal flat plates on low-drag airfoils
No Description digital.library.unt.edu/ark:/67531/metadc61370/
Pressure-Distribution Measurements of a Model of a Davis Wing Section with Fowler Flap Submitted by Consolidated Aircraft Corporation
Wing pressure distribution diagrams for several angles of attack and flap deflections of 0 degrees, 20 degrees, and 40 degrees are presented. The normal force coefficients agree with lift coefficients obtained in previous test of the same model, except for the maximum lifts with flap deflection. Pressure distribution measurements were made at Reynolds Number of about 6,000,000. digital.library.unt.edu/ark:/67531/metadc61480/
Pressure-distribution measurements of two airfoil models with Fowler flaps submitted by Consolidated Aircraft Corporation as alternative wing sections of the XB-32 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61481/
Tests of four models representing intermediate sections of the XB-33 airplane including sections with slotted flap and ailerons
No Description digital.library.unt.edu/ark:/67531/metadc61366/
Flight measurements of the effect of various amounts of aileron droop on the low-speed lateral-control characteristics of an observation airplane
No Description digital.library.unt.edu/ark:/67531/metadc279604/
Flight measurements of the effects of a wing leading-edge slot and other modifications on the stability, maximum lift, and high speed of an observation airplane
No Description digital.library.unt.edu/ark:/67531/metadc62501/
Characteristics of the BMW 801D2 automatic engine control as determined from bench tests
No Description digital.library.unt.edu/ark:/67531/metadc62109/
Variation with Mach Number of Static and Total Pressures Through Various Screens
Tests were conducted in the Langley 24-inch highspeed tunnel to ascertain the static-pressure and total-pressure losses through screens ranging in mesh from 3 to 12 wires per inch and in wire diameter from 0.023 to 0.041 inch. Data were obtained from a Mach number of approximately 0.20 up to the maximum (choking) Mach number obtainable for each screen. The results of this investigation indicate that the pressure losses increase with increasing Mach number until the choking Mach number, which can be computed, is reached. Since choking imposes a restriction on the mass rate of flow and maximum losses are incurred at this condition, great care must be taken in selecting the screen mesh and wire dimmeter for an installation so that the choking Mach number is. digital.library.unt.edu/ark:/67531/metadc62531/
Charts for the determination of wing torsional stiffness required for specified rolling characteristics or aileron reversal speed
No Description digital.library.unt.edu/ark:/67531/metadc61277/
Comparison of yaw characteristics of a single-engine airplane model with single-rotating and dual-rotating propellers
No Description digital.library.unt.edu/ark:/67531/metadc62165/
Wind-tunnel tests of two tapered wings with straight leading edges and with constant-chord center sections of different spans
No Description digital.library.unt.edu/ark:/67531/metadc61422/
The problem of longitudinal stability and control at high speeds
No Description digital.library.unt.edu/ark:/67531/metadc279426/
The knock-limited performance of several fuels blended with S-2 reference fuel
No Description digital.library.unt.edu/ark:/67531/metadc62382/
Wind-tunnel investigation of control-surface characteristics III : a small aerodynamic balance of various nose shapes used with a 30-percent-chord flap on an NACA 0009 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61531/
Wind-tunnel investigation of control-surface characteristics V : the use of a beveled trailing edge to reduce the hinge moment of a control surface
No Description digital.library.unt.edu/ark:/67531/metadc61519/
Tests of NACA 65(216)-420 and 66(218)-420 airfoils at high speeds
No Description digital.library.unt.edu/ark:/67531/metadc61374/
Wind tunnel tests of ailerons at various speeds IV : ailerons of 0.20 airfoil chord and true contour with 0.35 aileron-chord extreme blunt-nose balance on the NACA 23012 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61629/
Single-cylinder engine tests of porous chrome-plated cylinder barrels with special bore coatings for radial air-cooled engines
No Description digital.library.unt.edu/ark:/67531/metadc61909/
Fatigue tests of riveted joints : progress report of tests of 17S-T and 53S-T joints
No Description digital.library.unt.edu/ark:/67531/metadc61849/
Determination of the stability and control characteristics of a straight-wing, tailless fighter-airplane model in the Langley free-flight tunnel
No Description digital.library.unt.edu/ark:/67531/metadc61003/
Effect of wing modifications on the longitudinal stability of a tailless all-wing airplane model
No Description digital.library.unt.edu/ark:/67531/metadc61001/
Maximum lift coefficients of airplanes based on sum of wing and tail areas
No Description digital.library.unt.edu/ark:/67531/metadc60890/
Pressure distribution measurements on various surfaces of a 0.2375-scale model of the Douglas XA-26 airplane in the 19-foot pressure tunnel
No Description digital.library.unt.edu/ark:/67531/metadc61249/
Tests in the 19-foot pressure tunnel of a 1/2.75-scale model of the F4U-1 airplane with several balanced elevators, full-span flaps, and droppable gas tank
No Description digital.library.unt.edu/ark:/67531/metadc62595/
Charts for calculation of the critical compressive stress for local instability of idealized web- and T-stiffened panels
No Description digital.library.unt.edu/ark:/67531/metadc61300/
Numerical Evaluation of the Wake-Survey Equations for Subsonic Flow Including the Effect of Energy Addition
No abstract available. digital.library.unt.edu/ark:/67531/metadc62566/
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/
Simple curves for determining the effects of compressibility on pressure drop through radiators
No Description digital.library.unt.edu/ark:/67531/metadc62021/
Wind-tunnel investigation of a high-critical-speed fuselage scoop including the effects of boundary layer
No Description digital.library.unt.edu/ark:/67531/metadc61665/
Wind tunnel tests of a submerged-engine fuselage design
No Description digital.library.unt.edu/ark:/67531/metadc61660/
The effect of carburetor throttle settings on the velocity distribution at the outlet of a vaned and vaneless supercharger inlet elbow
No Description digital.library.unt.edu/ark:/67531/metadc62084/
Effect of changes in aspect ratio, side area, flight-path angle, and normal acceleration on lateral stability
No Description digital.library.unt.edu/ark:/67531/metadc60935/
Tank tests on the resistance and porpoising characteristics of three flying-boat hull models equipped with planing flaps
No Description digital.library.unt.edu/ark:/67531/metadc61790/
High-speed aerodynamic characteristics of a four-engine bomber airplane as determined from tests of a 0.075-scale model
No Description digital.library.unt.edu/ark:/67531/metadc62498/
High-speed aerodynamic characteristics of a four-engine transport airplane as determined from tests of a 0.075-scale model
No Description digital.library.unt.edu/ark:/67531/metadc61186/
Effect of varying percentages of exhaust gas on engine performance
No Description digital.library.unt.edu/ark:/67531/metadc62385/
Estimation of F-3 and F-4 knock-limited performance ratings for ternary and quaternary blends containing triptane or other high-antiknock aviation-fuel blending agents
No Description digital.library.unt.edu/ark:/67531/metadc62293/
An evaluation of the knock-limited performance of triptane
No Description digital.library.unt.edu/ark:/67531/metadc62312/
Lead susceptibility of paraffins, cycloparaffins, and olefins
No Description digital.library.unt.edu/ark:/67531/metadc62337/
Smoking characteristics of various fuels as determined by open-cup and laboratory-burner smoke tests
No Description digital.library.unt.edu/ark:/67531/metadc62548/
Investigation of air flow in right-angle elbows in a rectangular duct
No Description digital.library.unt.edu/ark:/67531/metadc62039/
Wind-tunnel tests of a dual-rotating propeller having one component locked or windmilling
No Description digital.library.unt.edu/ark:/67531/metadc62184/
Shear tests on DuPont explosive rivets with the countersunk head milled flush after expansion
No Description digital.library.unt.edu/ark:/67531/metadc61753/
Tensile Tests of NACA and Conventional Machine- Countersunk Flush Rivets
An investigation was conducted to determine and compare the tensile strength of NACA and conventional machine-countersunk flush rivets of several rivet-head angles and varying countersunk depth. The results of the investigation are presented in the form of curves that show the variation of the tensile strength of the rivet with the ratio of the sheet thickness to the rivet diameter. For the same rivet-head angle and for a given angle of c/d, the NACA rivets developed higher tensile strength than the conventional rivets. digital.library.unt.edu/ark:/67531/metadc61751/
The NACA impact basin and water landing tests of a float model at various velocities and weights
No Description digital.library.unt.edu/ark:/67531/metadc61795/
Variation of hydrodynamic impact loads with flight-path angle for a prismatic float at 3 degree trim and with a 22 1/2 degree angle of dead rise
No Description digital.library.unt.edu/ark:/67531/metadc61796/
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