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- Wind-tunnel investigation of horizontal tails II : unswept and 35 degree swept-back plan forms of aspect ratio 4.5
- No Description digital.library.unt.edu/ark:/67531/metadc64603/
- Wind-tunnel investigation of horizontal tails III : unswept and 35 degrees swept-back plan forms of aspect ratio 6
- No Description digital.library.unt.edu/ark:/67531/metadc57847/
- Wind-tunnel investigation of horizontal tails IV : unswept plan form of aspect ratio 2 and a two-dimensional model
- No Description digital.library.unt.edu/ark:/67531/metadc57810/
- Wind-tunnel investigation of horizontal tails V : 45 degree swept-back plan form of aspect ratio 2
- No Description digital.library.unt.edu/ark:/67531/metadc58200/
- Wind-tunnel investigation of icing of an engine cooling-fan installation
- No Description digital.library.unt.edu/ark:/67531/metadc55304/
- Wind-tunnel investigation of icing of an engine cooling-fan installation
- No Description digital.library.unt.edu/ark:/67531/metadc53468/
- Wind-tunnel investigation of jet-augmented flaps on a rectangular wing to high momentum coefficients
- No Description digital.library.unt.edu/ark:/67531/metadc56321/
- Wind-tunnel investigation of mutual interference loads on a supersonic bomber configuration and store during separation at mach numbers of 1.57, 1.77, and 2.01
- No Description digital.library.unt.edu/ark:/67531/metadc53097/
- Wind-Tunnel investigation of NACA 65,3-418 airfoil section with boundary-layer control through a single suction slot applied to a plain flap
- No Description digital.library.unt.edu/ark:/67531/metadc58235/
- Wind tunnel investigation of NACA 66(215)-216, 66,1-212, and 65(sub 1)-212 airfoils with 0.20-airfoil-chord split flaps
- No Description digital.library.unt.edu/ark:/67531/metadc61376/
- Wind-tunnel investigation of NACA 23012, 23021, and 23030 airfoils equipped with 40-percent-chord double slotted flaps
- Report presents the results of an investigation conducted in the NACA 7 by 10-foot win tunnel to determine the effect of the deflection of main and auxiliary slotted flaps on the aerodynamic section characteristics of large-chord NACA 23012, 23021, 23030 airfoils equipped with 40-percent-chord double slotted flaps. The complete aerodynamic section characteristics and envelope polar curves are given for each airfoil-flap combination. The effect of airfoil thickness is shown, and comparisons are made of single slotted flaps with double slotted flaps on each of the airfoils. digital.library.unt.edu/ark:/67531/metadc59972/
- Wind-tunnel investigation of NACA 23012, 23021, and 23030 airfoils with various sizes of split flap
- Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of large-chord NACA and 23021, and 23030 airfoils with split flaps 10, 20, 30, and 40 percent of the wing chord to determine the section aerodynamic characteristics of the airfoils as affected by airfoil thickness, flap chord, and flap deflection. The complete section aerodynamic characteristics of all the combinations tested are given in the form of graphs of lift, drag, and pitching-moment coefficients, and certain applications to aerodynamic design are discussed. digital.library.unt.edu/ark:/67531/metadc66326/
- Wind-tunnel investigation of NACA 23012 airfoil with various arrangements of slotted flaps
- An investigation was made in the NACA 7 by 10-foot wind tunnel of a large-chord NACA 23012 airfoil with several arrangements of 25.66 percent chord slotted flaps to determine the section aerodynamic characteristics as affected by slot shape, flap shape, flap location, and flap deflection. The flap position for maximum lift, the polars for arrangements considered favorable for take-off and climb, and the complete section aerodynamic characteristics for selected optimum arrangements were determined. A discussion is given of the relative merits of the various arrangement for certain selected criterions. A comparison is made of a slotted flap on the NACA 23021 airfoil with a corresponding slotted flap previously developed for the NACA 23012 airfoil. digital.library.unt.edu/ark:/67531/metadc66335/
- Wind-tunnel investigation of ordinary and split flaps on airfoils of different profile
- Report presents the results of wind tunnel tests of the Clark Y, the NACA 23012 and the NACA 23021 airfoils equipped with full-span ordinary flaps and with full-span simple split flaps. The principal object of the tests was to determine the characteristics of the airfoils with ordinary flaps and in addition, to determine the relative merits of the various airfoils when equipped with either ordinary flaps or with simple split flaps. The Clark Y airfoil was tested with 3 widths of ordinary flap, 10, 20, and 30 percent of the airfoil chord. The optimum width of the ordinary and the simple split flap based on the maximum lift attained with the Clark Y airfoil was then tested on each of the other two airfoils. digital.library.unt.edu/ark:/67531/metadc66212/
- Wind-tunnel investigation of perforated split flaps for use as dive brakes on a rectangular NACA 23012 airfoil
- No Description digital.library.unt.edu/ark:/67531/metadc61452/
- Wind-Tunnel Investigation of Perforated Split Flaps for Use as Dive Brakes on a Tapered NACA 23012 Airfoil
- Aerodynamic characteristics of a tapered NACA 23012 airfoil with single and double perforated split flaps have been determined in the NACA 7- by 10-foot wind tunnel. Dynamic pressure surveys were made behind the airfoil at the approximate location of the tail in order to determine the extent and location of the wake for several of the flap arrangements. In addition, computations have been made of an application of perforated double split flaps for use as fighter brakes. The results indicated that single or double perforated split flaps may be used to obtain satisfactory dive control without undue buffeting effects and that single or double perforated split flaps may also be used as fighter brakes. The perforated split flaps had approximately the same effects on the aerodynamic and wake characteristics of the tapered airfoil as on a comparable rectangular airfoil. digital.library.unt.edu/ark:/67531/metadc61454/
- Wind-tunnel investigation of plain ailerons for a wing with a full-span flap consisting of an inboard Fowler and an outboard retractable split flap
- No Description digital.library.unt.edu/ark:/67531/metadc61435/
- Wind-tunnel investigation of profile drag and lift of an intermediate wing section of the XP-51 airplane with beveled trailing-edge and contour ailerons
- No Description digital.library.unt.edu/ark:/67531/metadc61449/
- Wind tunnel investigation of rear underslung fuselage ducts
- No Description digital.library.unt.edu/ark:/67531/metadc61159/
- Wind-Tunnel Investigation of Rectangular Air-Duct Entrances in the Leading Edge of an NACA 23018 Wing, Special Report
- A preliminary investigation of a number of duct entrances of rectangular shape installed in the leading edge of a wing was conducted in the NACA 20-foot tunnel to determine the external drag, the available pressure, the critical Mach numbers, and the effect on the maximum lift. The results showed that the most satisfactory entrances, which had practically no effect on the wing characteristics, had their lips approximately in the vertical plane of the leading edge of the wing. This requirement necessitated extending the lips outside the wing contour for all except the small entrances. Full dynamic pressure was found to be available over a fairly wide range of angle of attack. The critical Mach number for a small entrance was calculated to be as high as that for the plain wing but was slightly lower for the larger entrances tested. digital.library.unt.edu/ark:/67531/metadc65078/
- Wind-tunnel investigation of rectangular and tapered NACA 23012 wings with plain ailerons and full-span split flaps
- An investigation was made to determine the aerodynamic properties of rectangular and tapered NACA 23012 wings with plain ailerons and a full-span split flap, the flap retracting ahead of the ailerons. Measurements were made of lift and drag and of pitching, rolling, yawing, and hinge moments for all conditions of full-span flaps neutral and deflected at different chord locations. The results of the tests showed that a 0.20c(sub w) full span split flap located at approximately the 0.75c(sub w) point gave higher lift coefficients than had previously been obtained with a conventional 0.20c(sub w) partial-span split flap of a length to permit satisfactory control with plain ailerons. Still higher lifts were obtained if the full-span flap, when deflected, was moved back to the aileron axis. Moving the flap back to the aileron, in general, improved the aileron characteristics over those with the flap retracted. The most promising arrangement of full-span split flap and plain aileron combination tested, both for high lift and lateral control, was the rectangular wing with 0.20c(sub w) deflected 60 degrees at the 0.90c(sub w) location with 0.10c(sub w) semispan ailerons. digital.library.unt.edu/ark:/67531/metadc54443/
- Wind-tunnel investigation of rounded horns and of guards on a horizontal tail surface
- No Description digital.library.unt.edu/ark:/67531/metadc61580/
- Wind-tunnel investigation of seven thin NACA airfoil sections to determine optimum double-slotted-flap configurations
- No Description digital.library.unt.edu/ark:/67531/metadc54815/
- Wind-tunnel investigation of several factors affecting the performance of a high-speed pursuit airplane with air-cooled radial engine
- No Description digital.library.unt.edu/ark:/67531/metadc53569/
- A wind tunnel investigation of several wingless missile configurations at supersonic speeds
- No Description digital.library.unt.edu/ark:/67531/metadc53213/
- A wind-tunnel investigation of several wingless missile configurations at supersonic speeds
- No Description digital.library.unt.edu/ark:/67531/metadc63800/
- Wind-Tunnel Investigation of Shielded Horn Balances and Tabs on a 0.7-Scale Model of XF6F Vertical Tail Surface
- Results of subject tests indicate the difficulty of obtaining closely balanced rudder surfaces for most tail assemblies with shielded horns and maintaining a near zero rate-of-change of hinge-moment coefficient without an additional balancing device. A comparison is made between shielded and unshielded horn test results. Pressure distribution and tuft tests of flow over different shaped horns showed higher critical speed for medium-taper nosed horn. The trim tab nose shape had little effect on tab test results. digital.library.unt.edu/ark:/67531/metadc61579/
- Wind-tunnel investigation of six shielded total-pressure tubes at high angles of attack subsonic speeds
- No Description digital.library.unt.edu/ark:/67531/metadc56102/
- Wind-tunnel investigation of split trailing-edge lift and trim flaps on a tapered wing with 23 degree sweepback
- No Description digital.library.unt.edu/ark:/67531/metadc55361/
- Wind-tunnel investigation of spoiler, deflector, and slot lateral-control devices on wings with full-span split and slotted flaps
- Report presents the results of an extensive investigation made in the NACA 7 by 10-foot wind tunnel of spoiler, deflector, and slot types of lateral-control device on wings with full-span split and slotted flaps. The static rolling and yawing moments were determined for all the devices tested, and the static hinge moments and the time response were determined for a few devices of each type. digital.library.unt.edu/ark:/67531/metadc66367/
- Wind-tunnel investigation of stall control by suction through a porous leading edge on a 37 degree sweptback wing of aspect ratio 6 at Reynolds numbers from 2.50 x 10(exp 6) to 8.10 x 10(exp 6)
- No Description digital.library.unt.edu/ark:/67531/metadc59463/
- Wind-tunnel investigation of static lateral and longitudinal stability characteristics of a 1/62-scale model of the X-1E airplane at combined angles of attack and sideslip at supersonic speeds
- No Description digital.library.unt.edu/ark:/67531/metadc63680/
- Wind-tunnel investigation of tapered wings with ordinary ailerons and partial-span split flaps
- Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel to determine the aerodynamic properties of tapered wings having partial-span flaps for high lift and ordinary ailerons for lateral control. Each of two Clark-y wings, tapered 5:1 and 5:3, was equipped with partial-span split flaps of two lengths and with ordinary ailerons extending from the outboard ends of the flap to the wing tips. Measurements of wing forces and moments and of aileron hinge moments were made for the two conditions of flaps neutral and deflected. digital.library.unt.edu/ark:/67531/metadc66269/
- Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane
- No Description digital.library.unt.edu/ark:/67531/metadc64250/
- Wind-tunnel investigation of the aerodynamic balancing of upper-surface ailerons and split flaps
- This report presents the results of wind tunnel tests to determine the effectiveness of various methods of reducing the high control forces of unbalanced upper-surface ailerons and of unbalanced split flaps. digital.library.unt.edu/ark:/67531/metadc66207/
- Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combination at high subsonic speeds : sweep series
- No Description digital.library.unt.edu/ark:/67531/metadc59275/
- Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds : aspect-ratio series
- No Description digital.library.unt.edu/ark:/67531/metadc59105/
- Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds : taper-ratio series
- No Description digital.library.unt.edu/ark:/67531/metadc56348/
- Wind-tunnel investigation of the aerodynamic characteristics in pitch of wing-fuselage combinations at high subsonic speeds : taper-ratio series
- No Description digital.library.unt.edu/ark:/67531/metadc59594/
- Wind-Tunnel Investigation of the Aerodynamic Characteristics of a 0.07-Scale Model of the North American MX-770 Missile
- No Description digital.library.unt.edu/ark:/67531/metadc53257/
- Wind-tunnel investigation of the aerodynamic characteristics of a 1/15-scale model of the Northrop MX-775A missile
- No Description digital.library.unt.edu/ark:/67531/metadc59000/
- A wind-tunnel investigation of the aerodynamic characteristics of a full-scale supersonic-type three-blade propeller at Mach numbers to 0.96
- An investigation of the characteristics of a full-scale supersonic-type propeller has been made in the Langley 16-foot transonic tunnel with the 6000-horsepower propeller dynamometer. The tests covered a range of blade angles from 20.2 degrees to 60.2 degrees at forward Mach numbers up to 0.96. The results showed that envelope efficiency at an advance ratio of 2.8 decreased from 86 percent to 72 percent when the forward Mach number was increased from 0.70 to 0.96. A comparison of the experimental results with calculated results showed that maximum propeller efficiency can be calculated with good accuracy by using ordinary subsonic strip theory when the blade-section speeds are supersonic. The investigation also showed favorable power-absorption properties of the supersonic-type propeller at high speeds. digital.library.unt.edu/ark:/67531/metadc60796/
- A wind-tunnel investigation of the aerodynamic characteristics of a full-scale sweptback propeller and two related straight propellers
- No Description digital.library.unt.edu/ark:/67531/metadc64657/
- Wind-tunnel investigation of the aerodynamic characteristics of a series of swept, highly tapered thin wings at transonic speeds : transonic bumb method
- No Description digital.library.unt.edu/ark:/67531/metadc62832/
- Wind-tunnel investigation of the air load distribution on two combinations of lifting surface and fuselage
- No Description digital.library.unt.edu/ark:/67531/metadc55235/
- Wind-tunnel investigation of the behavior of parachutes in close proximity to one another
- No Description digital.library.unt.edu/ark:/67531/metadc62199/
- Wind-tunnel investigation of the boundary layer and wake and their relation to airfoil characteristics.NACA 65(sub 1)-012 airfoil with a true contour flap and a beveled-trailing-edge flap
- No Description digital.library.unt.edu/ark:/67531/metadc54436/
- Wind-tunnel investigation of the boundary layer on an NACA 0009 airfoil having 0.25- and 0.50- airfoil chord plain sealed flaps
- No Description digital.library.unt.edu/ark:/67531/metadc54904/
- Wind-Tunnel Investigation of the Characteristics of Blunt-Nose Ailerons on a Tapered Wing
- Characteristics are determined for various modifications of 0.155-chord blunt-nose aileron on semispan model of tapered fighter plane wing. Ailerons with 40 percent nose balance reduced high-speed stick forces. Increased balance chord increases effectiveness and reduces high-speed stick forces. Increased balance chord increases effectiveness and reduces adverse effects of gap at aileron hose. Increase of nose radii increased negative slope of curve hinge-movement coefficient plotted against deflection. Extended deflection range decreased aileron effectiveness for small deflections but increased it at large deflections. Peak pressures at noses of ailerons are relatively high at moderate deflections. digital.library.unt.edu/ark:/67531/metadc61611/
- Wind-tunnel investigation of the contribution of a vertical tail to the directional stability of a fighter-type airplane
- Contributions of vertical tail and fuselage to directional stability are determined from pressure distributions measured over wide ranges of angle of attack and angle of yaw with stabilizer in each of three vertical positions, with stabilizer removed and with both stabilizer and vertical tail removed. Results point out inadequacies of current design methods and show that more accurate methods must treat separately contributions of vertical tail, fuselage area above stabilizer, and fuselage area below stabilizer. digital.library.unt.edu/ark:/67531/metadc55711/