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  Partner: UNT Libraries Government Documents Department
 Resource Type: Report
 Decade: 1950-1959
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

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

Date: February 26, 1951
Creator: Stivers, Louis S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: February 26, 1951
Creator: Stivers, Louis S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: December 13, 1950
Creator: Stivers, Louis S , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at Mach numbers of 1.5 and 2.0 of a canard missile configuration

Wind-tunnel investigation at Mach numbers of 1.5 and 2.0 of a canard missile configuration

Date: May 11, 1951
Creator: Spahr, J Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Wind-tunnel investigation at Mach numbers of 2.0 and 2.9 of several configurations of a supersonic ram-jet test vehicle

Wind-tunnel investigation at Mach numbers of 2.0 and 2.9 of several configurations of a supersonic ram-jet test vehicle

Date: August 18, 1950
Creator: Spahr, J Richard
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: April 6, 1951
Creator: Johnson, Harold S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: August 26, 1954
Creator: Wetzel, Benton E.
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: April 28, 1955
Creator: Wetzel, Benton E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: April 5, 1954
Creator: Smith, Williard G.
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
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

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

Date: November 15, 1954
Creator: Smith, Willard G
Description: None
Contributing Partner: UNT Libraries Government Documents Department