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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
Wind-tunnel investigation at low speed of a wing having 63 degree sweepback and a drooped tip
No Description digital.library.unt.edu/ark:/67531/metadc61476/
Wind-tunnel investigation at low speed of a wing swept-back 63 degrees and twisted and cambered for a uniform load at a lift coefficient of 0.5
No Description digital.library.unt.edu/ark:/67531/metadc58464/
Wind-tunnel investigation at low speed of a wing swept back 63 degrees and twisted and cambered for uniform load at a lift coefficient of 0.5 and with a thickened tip section
No Description digital.library.unt.edu/ark:/67531/metadc58676/
Wind Tunnel Investigation at Low Speed of Aerodynamic Characteristics of Army Chemical Corps Model E-112 Bomblets with Span Chord Ratio of 2 - 1
An experimental investigation has been made in the Langley stability tunnel to determine the aerodynamic characteristics of the Army Chemical Corps model E-112 bomblets with span-chord ratio of 2:1. A detailed analysis has not been made; however, the results showed that all the models were spirally unstable and that a large gap between the model tips and end plates tended to reduce the instability. digital.library.unt.edu/ark:/67531/metadc53264/
Wind-tunnel investigation at low speed of an unswept untapered semispan wing of aspect ratio 3.13 equipped with various 25-percent-chord plain flaps
No Description digital.library.unt.edu/ark:/67531/metadc55527/
Wind-tunnel investigation at low speed of effect of size and position of closed air ducts on static longitudinal and static lateral stability characteristics of unswept-midwing models having wings of aspect ratio 2, 4, and 6
No Description digital.library.unt.edu/ark:/67531/metadc57754/
Wind-tunnel investigation at low speed of effects of sideslip on static longitudinal trim and static lateral stability characteristics of three fighter-type airplane models
No Description digital.library.unt.edu/ark:/67531/metadc62639/
Wind-tunnel investigation at low speed of sideslipping, rolling, yawing, and pitching characteristics for a model of a 45 degree swept-wing fighter-type airplane
No Description digital.library.unt.edu/ark:/67531/metadc61550/
Wind-tunnel investigation at low speed of static and yawing characteristics of a 0.085-scale model of the Chance Vought XF8U-1 airplane : TED No. NACA DE 392
No Description digital.library.unt.edu/ark:/67531/metadc60283/
Wind-tunnel investigation at low speed of the aerodynamic characteristics of the Army Chemical Corps model E112 bomblets
No Description digital.library.unt.edu/ark:/67531/metadc61977/
Wind Tunnel Investigation at Low Speed of the Aerodynamic Characteristics of the Army Chemical Corps Model E112 Bomblets
No Description digital.library.unt.edu/ark:/67531/metadc53268/
Wind-tunnel investigation at low speed of the effects of chordwise wing fences and horizontal-tail position on the static longitudinal stability characteristics of an airplane model with a 35 degree sweptback wing
Low-speed tests of a model with a wing swept back 35 degrees at the 0.33-chord line and a horizontal tail located well above the extended wing-chord plane indicated static longitudinal instability at moderate angles of attack for all configurations tested. An investigation therefore was made to determine whether the longitudinal stability could be improved by the use of chordwise wing fences, by lowering the horizontal tail, or by a combination of both. The results of the investigation showed that the longitudinal stability characteristics of the model with slats retracted could be improved at moderate angles of attack by placing chordwise wing fences at a spanwise station of about 73 percent of the wing semispan from the plane of symmetry provided the nose of the fence extended slightly beyond or around the wing leading edge. digital.library.unt.edu/ark:/67531/metadc60578/
Wind-tunnel investigation at low speed of the effects of symmetrical deflection of half-delta tip controls on the damping in roll and yawing moment due to rolling of a triangular-wing model
No Description digital.library.unt.edu/ark:/67531/metadc58953/
Wind-tunnel investigation at low speed of the lateral control characteristics of ailerons having three spans and three trailing-edge angles on a semispan wing model
No Description digital.library.unt.edu/ark:/67531/metadc55008/
Wind-tunnel investigation at low speed of the lateral control characteristics of an unswept untapered semi-span wing of aspect ratio 3.13 equipped with various 25-percent-chord plain ailerons
No Description digital.library.unt.edu/ark:/67531/metadc55591/
Wind-Tunnel Investigation at Low Speed of the Pitching Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373
An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the pitching stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient, control deflections, and propeller blade angle were investigated. The tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper. digital.library.unt.edu/ark:/67531/metadc64654/
Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373
An experimental investigation has been conducted in the Langley stability tunnel at low speed to determine the rolling stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller blade angle were investigated for the complete model. Most of the tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this paper. digital.library.unt.edu/ark:/67531/metadc64736/
Wind-tunnel investigation at low speed of the rolling stability derivatives of a 1/10-scale model of the douglas a4d-1 airplane
No Description digital.library.unt.edu/ark:/67531/metadc53038/
Wind-tunnel investigation at low speed of the rolling stability derivatives of a 1/10-scale model of the Douglas A4D-1 airplane : TED No. NACA DE 389
No Description digital.library.unt.edu/ark:/67531/metadc60822/
Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109
An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution. digital.library.unt.edu/ark:/67531/metadc64698/
Wind-Tunnel Investigation at Low Speed of the Static Longitudinal and Lateral Stability Characteristics of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane
An experimental investigation has been made in the Langley stability tunnel at low speed to determine the static longitudinal and lateral stability characteristics of a l/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller-blade angle were investigated briefly for the complete model. Most of the tests were made through an angle-of-attack range from about -4 deg. to 29 deg, and the thrust-coefficient range was from 0 t o 0.7. In order to expedite distribution of these data to interested persons, no analysis of the data has been prepared for this report,. digital.library.unt.edu/ark:/67531/metadc64911/
Wind-Tunnel Investigation at Low Speed of the Yawing, Pitching, and Static Stability Characteristics of a 1/10-Scale Model of the Grumman F9F-9 Airplane, TED No. NACA AD 3109
An experimental investigation has been made in the Langley stability tunnel to determine the low-speed yawing, pitching, and static stability characteristics of a 1/10-scale model of the Grumman F9F-9 airplane. Tests were made to determine the effects of duct-entrance-fairing plugs on the static lateral and longitudinal stability characteristics of the complete model in the clean condition. The remaining tests were concerned with determining tail contributions as well as the effect of duct-entrance-fairing plugs, slats, flaps, and landing gear on the yawing and pitching stability derivatives. These data are presented without analysis in order to expedite distribution. digital.library.unt.edu/ark:/67531/metadc64692/
Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/9-Scale Powered Model of the Convair XFY-1 Vertically Rising Airplane, TED No. NACA DE 373
An experimental investigation has been conducted in the Langley stability tunnel at low speed to deter+nine the yawing stability derivatives of a 1/9-scale powered model of the Convair XFY-1 vertically rising airplane. Effects of thrust coefficient were investigated for the complete model and for certain components of the model. Effects of control deflections and of propeller blade angle were investigated for the complete model. Most of the tests were made through an angle-of-attack range from about -4deg to 29deg, and the thrust coefficient range was from 0 to 0.7. In order to expedite distribution of these data, no analysis of the data has been prepared for this. digital.library.unt.edu/ark:/67531/metadc64725/
Wind-tunnel investigation at low speed of the yawing stability derivatives of a 1/10-scale model of the douglas a4d-1 airplane
No Description digital.library.unt.edu/ark:/67531/metadc53039/
Wind-tunnel investigation at low speed of the yawing stability derivatives of a 1/10-scale model of the Douglas A4D-1 airplane : TED No. NACA DE 389
No Description digital.library.unt.edu/ark:/67531/metadc60876/
A wind-tunnel investigation at low speed of various lateral controls on a 45 degree swept-back wing
No Description digital.library.unt.edu/ark:/67531/metadc58232/
Wind-tunnel investigation at low speeds of flight characteristics of a sweptback-wing jet-transport airplane model equipped with an external-flow jet-augmented slotted flap
No Description digital.library.unt.edu/ark:/67531/metadc57416/
A wind-tunnel investigation at low speeds of the aerodynamic characteristics of various spoiler configurations on a thin 60 degrees delta wing
No Description digital.library.unt.edu/ark:/67531/metadc59500/
Wind-tunnel investigation at low speeds of the pitching derivatives of untapered swept wings
No Description digital.library.unt.edu/ark:/67531/metadc57735/
Wind-tunnel investigation at low speeds of various plug-aileron and lift-flap configurations on a 42 degree sweptback semispan wing
No Description digital.library.unt.edu/ark:/67531/metadc57942/
Wind-tunnel investigation at low speeds to determine flow-field characteristics and ground influence on a model with jet-augmented flaps
No Description digital.library.unt.edu/ark:/67531/metadc56674/
Wind-tunnel investigation at low speeds to determine the effect of aspect ratio and end plates on a rectangular wing with jet flaps deflected 85 degrees
No Description digital.library.unt.edu/ark:/67531/metadc56298/
Wind-tunnel investigation at Mach 1.9 of multijet-missile base pressures
No Description digital.library.unt.edu/ark:/67531/metadc61070/
Wind-tunnel investigation at Mach numbers from 0.6 to 1.4 of several ejected pilot-seat models
No Description digital.library.unt.edu/ark:/67531/metadc64259/
Wind-tunnel investigation at Mach numbers from 0.8 to 1.4 of static longitudinal and lateral-directional characteristics of an unswept-wing airplane model
No Description digital.library.unt.edu/ark:/67531/metadc62780/
Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps : flaps deflected in combination
No Description digital.library.unt.edu/ark:/67531/metadc58709/
Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - leading-edge flaps deflected
No Description digital.library.unt.edu/ark:/67531/metadc58712/
Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - trailing-edge flaps deflected
No Description digital.library.unt.edu/ark:/67531/metadc58635/
Wind-tunnel investigation at Mach numbers of 1.5 and 2.0 of a canard missile configuration
No Description digital.library.unt.edu/ark:/67531/metadc58822/
Wind-tunnel investigation at Mach numbers of 2.0 and 2.9 of several configurations of a supersonic ram-jet test vehicle
No Description digital.library.unt.edu/ark:/67531/metadc58541/
Wind-tunnel investigation at subsonic and low transonic speeds of the effects of aileron span and spanwise location on the rolling characteristics of a test vehicle with three untapered 45 degree sweptback wings
No Description digital.library.unt.edu/ark:/67531/metadc58750/
Wind-tunnel investigation at subsonic and supersonic speeds of a fighter model employing a low-aspect-ratio unswept wing and a horizontal tail mounted well above the wing plane-lateral and directional stability
No Description digital.library.unt.edu/ark:/67531/metadc60810/
Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Fighter Model Employing a Low-aspect-ratio Unswept Wing and a Horizontal Tail Mounted Well above the Wing Plane - Lateral and Directional Stability
The static lateral- and directional-stability characteristics of a high-speed fighter-type airplane, obtained from wind-tunnel tests of a model, are presented. The model consisted of a thin, unswept wing of aspect ratio 2.3 and taper ratio 0.385, a body, and a horizontal tail mounted in a high position on a vertical tail. Rolling-moment, yawing moment, and cross-wind-force coefficients are presented for a range of sideslip angles of -5 deg. to +5 deg, for Mach numbers of 0.90, 1.45, and 1.90. Data are presented which show the effects on the lateral and directional stability of: (1) component parts of the complete model, (2) modification of the empennage so as to provide different heights of the horizontal tail above the wing plane, (3) angle of attack, and (4) dihedral of the wing. digital.library.unt.edu/ark:/67531/metadc65424/
Wind-tunnel investigation at subsonic and supersonic speeds of a fighter model employing a low-aspect-ratio unswept wing and a horizontal tail mounted well above the wing plane - longitudinal stability and control
No Description digital.library.unt.edu/ark:/67531/metadc60776/
Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Fighter Model Employing a Low-Aspect-Ratio Unswept Wing and a Horizontal Tail Mounted Well Above the Wing Plane - Longitudinal Stability and Control
Experimental results showing the static longitudinal-stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio unswept wing and an all-movable horizontal tail are presented. The investigation was made over a Mach number range from 0.60 to 0.90 and from 1.35 to 1.90 at a constant Reynolds number of 2.40 million, based on the wing mean aerodynamic chord. Because of the location of the horizontal tail at the tip of the vertical tail, interference was noted between the vertical tail and the horizontal tail and between the wing and the horizontal tail. This interference produced a positive pitching-moment coefficient at zero lift throughout the Mach number range of the tests, reduced the change in stability with increasing lift coefficient of the wing at moderate lift coefficients in the subsonic speed range, and reduced the stability at low lift coefficients at high supersonic speeds. The lift and pitching-moment effectiveness of the all movable tail was unaffected by the interference effects and was constant throughout the lift-coefficient range of the tests at each Mach number except 1.90. digital.library.unt.edu/ark:/67531/metadc65414/
Wind-tunnel investigation at subsonic and supersonic speeds of a model of a tailless fighter airplane employing a low-aspect-ratio swept-back wing : effects of external fuel tanks and rocket packets on the drag characteristics
No Description digital.library.unt.edu/ark:/67531/metadc64703/
Wind-tunnel Investigation at Subsonic and Supersonic Speeds of a Model of a Tailless Fighter Airplane Employing a Low-aspect-ratio Swept-back Wing-stability and Control
Subsonic and supersonic wind tunnel study of low aspect ratio sweptback wing tailless fighter aircraft model/stability and control. digital.library.unt.edu/ark:/67531/metadc52893/
Wind-tunnel investigation at transonic speeds of a jet control on a 35 degree swept wing : transonic-bump method
No Description digital.library.unt.edu/ark:/67531/metadc61814/
Wind-tunnel investigation at transonic speeds of a jet control on an 80 degree delta-wing missile
No Description digital.library.unt.edu/ark:/67531/metadc62169/
Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing
No Description digital.library.unt.edu/ark:/67531/metadc59908/