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  Partner: UNT Libraries Government Documents Department
 Collection: National Advisory Committee for Aeronautics Collection
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
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-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 - 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 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 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/
Wind-tunnel investigation of 20-percent-chord plain and Frise ailerons on an NACA 23012 airfoil
No Description digital.library.unt.edu/ark:/67531/metadc61460/
Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds Several Combinations of the Tail with Each of Two Foreshortened Body Segments
An investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numbers of 1.62 and 1.96 of a partial-span body with one tail surface, designed for use on the Hughes Falcon (MX-904) missile. The present paper extends the work reported in NACA-RM-SL50E10. Force and moment data including elevator hinge moment were obtained for the conditions of the tail in the presence of a small segment of the fore-shortened body, in the presence of a semi-span body and attached to a semi-span body, and for the condition of the foreshortened semi-span body alone. digital.library.unt.edu/ark:/67531/metadc64672/
Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds. Tail Attached to a Segment of the Foreshortened Body
No Description digital.library.unt.edu/ark:/67531/metadc53247/
Wind-Tunnel Investigation of a 1/5-Scale Model of the Ryan XF2R Airplane
Wind-tunnel tests on a 1/5-scale model of the Ryan XF2R airplane were conducted to determine the aerodynamic characteristics of the air intake for the front power plant, a General Electric TG-100 gas turbine, and to determine the stability and control characteristics of the airplane. The results indicated low-dynamic-pressure recover3- for the air intake to the TG-100 gas turbine ~rith the standard propeller in operation. Propeller cuffs were designed and tested for the purpose of imp~oving the dynamic-pressure recovery. Data obtained with the cuffs installed and the gap between the spinner an& the cuff sealed indicated a substantial gain in dynamic pressure recovery over that obtained with the standard propeller and with the cuffed propeller unsealed. Stability and control tests were conducted with the sealed cuffs installed on the propeller. The data from these tests indicated the following unsatisfactory characteristics for the airplane: 1. Marginal static longitudinal stability. 2. Inadequate directional stability and control. 3. Rudder-pedal-force reversal in the climb condition. 4. Negative dihedral effect in the power-on approach and wave-off conditions. digital.library.unt.edu/ark:/67531/metadc65578/
Wind-tunnel investigation of a 1/6-scale model of the Bumblebee XPM missile at high subsonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc53162/
Wind-tunnel investigation of a 1/6-scale model of the Bumblebee XPM missile at high subsonic speeds
No Description digital.library.unt.edu/ark:/67531/metadc58633/
Wind-Tunnel Investigation of a 1/15-Scale Model of the Republic MX-1554 Airplane at Mach Numbers of 1.45 and 1.90
This report presents the results of a wind-tunnel investigation of a 1/15-scale model of the Republic MX-1554 airplane at Mach numbers of 1.45 and 1.90 and at a Reynolds number of 3.0 million based on the mean aerodynamic chord of the wing. Tests were conducted to determine the static longitudinal and lateral stability of the model and the control effectiveness of the all-movable tail, elevators, rudder, aileron, and spoiler. All the results of this investigation are presented in graphic form and, in addition, the basic data have been cross-plotted to show the angle of attack, control deflection, and drag coefficient for the model balanced by the movable tail or the elevators. The primary control-effectiveness characteristics are also cross-plotted for all the controls tested. The results are presented without analysis or discussion to expedite publication. digital.library.unt.edu/ark:/67531/metadc59763/
Wind-tunnel investigation of a 1/20-scale powered model of a four-engine transport airplane
No Description digital.library.unt.edu/ark:/67531/metadc61210/
Wind-Tunnel Investigation of a 1/60-Scale Model of the Republic MX-1554 Airplane at a Mach Number of 2.85
No Description digital.library.unt.edu/ark:/67531/metadc53260/
Wind-tunnel investigation of a 45 degree sweptback wing having a symmetrical root and a highly cambered tip, including the effects of fences and lateral controls
No Description digital.library.unt.edu/ark:/67531/metadc60501/
Wind-tunnel investigation of a beveled aileron shape designed to increase the useful deflection range
No Description digital.library.unt.edu/ark:/67531/metadc61648/
Wind-Tunnel Investigation of a Full-Scale Model of the Hughes MX-904 Missile
A wind-tunnel investigation has been conducted to determine the stability and control characteristics of a full-size model of the Hughes MX-904 missile. Aerodynamic characteristics of the complete model through moderate ranges of angles of attack and yaw, with an additional test made through an angle of attack of 180 degrees, are presented. The effects of horizontal tail deflection are also included. digital.library.unt.edu/ark:/67531/metadc64791/
Wind-tunnel investigation of a full-span retractable flap in combination with full-span plain and internally balanced ailerons on a tapered wing
No Description digital.library.unt.edu/ark:/67531/metadc61420/