Derivative Measurements and Flutter Tests on a Model Tapered Wing
نویسنده
چکیده
منابع مشابه
Tests at Subsonic Speeds on a Half-Wing with a Fan Engine Nacelle
SUMMARY Flutter tests have been made on a half-wing model with a fan-engine nacelle attached by a pylon at an inboard section. The model was nominally rigid and flexibilities in pitch and roll were introduced at the root. Measurements were made of the flutter characteristics of the model at Mach numbers of 0.6 and 0.8 over a range of dynamic pressures using three different methods of analysis. ...
متن کاملFlutter Analysis of a Low Aspect Ratio Swept- Back Trapezoidal Wing at Low Subsonic Flow
A linear, aeroelastic analysis of a low aspect ratio swept back trapezoidal wing modeled as a cantilever plate is presented. An analytical and numerical formulation for both the aerodynamic forcing and structural response of the wing was developed. The analytical model uses a three dimensional time domain vortex lattice aerodynamic method. A Rayleigh-Ritz approach has been used to transfer equa...
متن کاملAIAA 95-3943 Interactive Flutter Analysis and Parametric Study for Conceptual Wing Design
An interactive computer program was developed for wing flutter analysis in the conceptual design stage. The objective was to estimate the flutter instability boundary of a flexible cantilever wing, when well defined structural and aerodynamic data are not available, and then study the effect of change in Mach number, dynamic pressure, torsional frequency, sweep, mass ratio, aspect ratio, taper ...
متن کاملMeasurements of Control-Surface Oscillatory Derivatives on a Sweptback, Tapered Model Wing in two Transonic Tunnels
Results of measurements of control-surface oscillatory derivatives on a sweptback, tapered half-model of a lifting surface of aspect ratio 2 are presented. The measurements were obtained during the development of a derivative rig which measures normal force, pitching moment, wing bending moment and hinge moment due to control surface oscillation. They were made in the 18 in. × 14 in. (0.46 m × ...
متن کاملAn Interactive Software for Conceptual Wing Flutter Analysis and Parametric Study
An interactive computer program was developed for wing flutter analysis in the conceptual design stage. The objective was to estimate the flutter instability boundary of a flexible cantilever wing, when well defined structural and aerodynamic data are not available, and then study the effect of change in Mach number, dynamic pressure, torsional frequency, sweep, mass ratio, aspect ratio, taper ...
متن کامل