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NACA-TN-1581: Approximate relations and charts for low-speed stability derivatives of swept wings
Abstract: Contains derivations, based on a simplified theory, of approximate relations for low-speed stability derivatives of swept wings. Method accounts for the effects and, in most cases, taper ratio. Charts, based on the derived ...
NACA-TN-2114: Theoretical lift and damping in roll of thin wings with arbitrary sweep and taper at supersonic speeds: supersonic leading and trailing edges
Abstract: The analysis is limited to wings of vanishingly small thickness that have zero camber. The results are valid only for a range of supersonic speeds in which the components of the free-stream velocity normal to the leading and trailing edges are supersonic. These conditions are now commonly expressed by the term "supersonic leading and trailing edges...
NACA-TN-1468: Low-speed static stability and damping-in-roll characteristics of some swept and unswept low-aspect-ratio wings
Abstract: INTRODUCTION
The recent trend toward the use of low-aspect-ratio wings for high-speed flight requires that the low-speed stability and control characteristics of such configurations be determined. Some work has been ...
The recent trend toward the use of low-aspect-ratio wings for high-speed flight requires that the low-speed stability and control characteristics of such configurations be determined. Some work has been ...
NACA-TR-1150: Considerations on the effect of wind-tunnel walls on oscillating air forces for two-dimensional subsonic compressible flow
Abstract: This report treats the effect of wind-tunnel walls on the oscillating two-dimensional air forces in a compressible medium. The walls are simulated by the usual method of placing images at appropriate distances above and ...
NACA-TN-1669: Investigation at Low Speeds of the Effect of Aspect Ratio and Sweep on Static and Yawing Stability Derivatives of Untapered Wings
Abstract: A low-scale wind-tunnel investigation was conducted in both straight and. yawing flow to determine the effects of aspect ratio and sweep (when varied independently) on the static and. yawing stability derivatives for a ...
NACA-TM-1225: Test Report on Three- and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (Partial Report: Trapezoidal Wing)
Abstract: The present report, which forms the first of six articles on experiments with airfoils of aspect ratio from 1 to 3 and various planforms, deals with the three- and six-component measurements made on the trapezoidal wing ...
NACA-TN-2010: Effect of horizontal tail on low-speed static lateral stability characteristics of a model having 45 degree sweptback wing and tail surfaces
Abstract: An investigation has been conducted in the Langley stability tunnel to determine the effects of changes in horizontal-tail size and location on the static lateral stability characteristics of a complete model with wing and ...
NACA-TN-1050: Wind-tunnel investigation of end-plate effects of horizontal tails on a vertical tail compared with available theory
Abstract: A vertical-tail model with stub fuselage was tested in combination with various simulated horizontal tails to determine the effect of horizontal-tail span and location on the aerodynamic characteristics of the vertical ...
NACA-ACR-5D28: An additional investigation of the high-speed lateral-control characteristics of spoilers
Abstract: INTRODUCTION
Previous tests (reference 1) showed that a spoiler in front of a conventional aileron will increases the rolling moment as well as decrease the stick force. At high spoods, even a small ...
Previous tests (reference 1) showed that a spoiler in front of a conventional aileron will increases the rolling moment as well as decrease the stick force. At high spoods, even a small ...
NACA-MR-L5L11: Two-dimensional wind-tunnel investigation of two NACA low-drag airfoil sections equipped with slotted flaps and a plain NACA low-drag airfoil section for XF6U-1 airplane
Abstract: INTRODUCTION
At the request of the Bureau of Aeronautics, Navy Department, test were conducted in the Langley two-dimensional, low-turbulence tunnels of three 24-inch-chord airfoil models representing ...
At the request of the Bureau of Aeronautics, Navy Department, test were conducted in the Langley two-dimensional, low-turbulence tunnels of three 24-inch-chord airfoil models representing ...