12 research outputs found
The Aerodynamic Characteristics Throughout the Subsonic Speed Range of a Thin, Sharp-edged Horizontal Tail of Aspect Ratio 4 Equipped with a Constant-chord Elevator
The Lateral Control Characteristics of Constant-percent-chord Trailing-edge Elevons on a Pointed Wing of Aspect Ratio 2 at Mach Numbers up to 0.95
Subsonic static longitudinal stability and control characteristics of a wing-body combination having a pointed wing of aspect ratio 2 with constant-percent-chord trailing-edge elevons
Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-foot Pressure Wind Tunnel IV : the Effect of a Constant-chord Leading-edge Flap at High Subsonic Speeds
The Static and Dynamic-rotary Stability Derivatives at Subsonic Speeds of an Airplane Model with an Unswept Wing and a High Horizontal Tail
Wind-tunnel measurements at subsonic speeds of the static and dynamic-rotary stability derivatives of a triangular-wing airplane model having a triangular vertical tail
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NACA Research Memorandums
From Introduction: "Recent investigations have indicated several wing plan forms, wing sections, and wing-body-tail combinations suitable for flight at supersonic speeds. One such lifting surface, a thin, sharp-edged without sweep of aspect ratio 4 and taper ratio 0.5, has been the subject of an investigation in the Ames 12-foot pressure wind tunnel. The aim of the investigation was to determine the aerodynamic characteristics of such a wing plan form throughout the range of subsonic Mach numbers up to 0.94.
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NACA Research Memorandums
Report presenting an investigation to determine the lateral control characteristics of constant-percent-chord trailing-edge elevons on a tailless wing-body combination with a pointed wing of aspect ratio 2. The effectiveness of inset tabs in reducing the elevon hinge moment was also determined. Results include the lift, drag, pitching moment, rolling moment, elevon hinge moment, tab moment, elevon load, and center of pressure of elevon load
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NACA Research Memorandums
Report presenting an investigation to determine the static longitudinal stability and control characteristics of a tailless wing-body combination with a pointed wing of aspect ratio 2 and trailing-edge elevons. The effectiveness of inset tabs in reducing the elevon hinge moment was also determined. Results regarding the lift, drag, pitching moment, elevon hinge moment, tab hinge moment, elevon load, and center of pressure of elevon load are provided
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NACA Research Memorandums
Report presenting wind-tunnel tests of a semispan model of a thin sharp-edged unswept wing of aspect ratio 4 and taper ratio 0.5 equipped with a full-span, constant-chord, leading-edge flap. The effectiveness of the leading-edge flap in improving the lift-drag ratio of the wing was investigated over a range of Mach and Reynolds numbers. Results regarding the lift characteristics, drag characteristics, pitching-moment characteristics, and lift-drag ratio are provided