Full-Scale Testing of Active Flow Control Applied to a Vertical Tail
نویسندگان
چکیده
منابع مشابه
Experimental Investigation of the Effect of Vertical Tail on the Flow Field and Aerodynamic Forces of a fighter Model
An intensive experimental investigation was conducted to study the effect of vertical tail, single and twin (with different cant angles) on the flow field and the corresponding aerodynamic forces and moments of a model of a fighter A/C. Aerodynamic forces under different flight conditions and different vertical tail settings were measured in a supersonic wind tunnel. Furthermore, effects of ver...
متن کاملExperimental Investigation of the Effect of Vertical Tail on the Flow Field and Aerodynamic Forces of a fighter Model
An intensive experimental investigation was conducted to study the effect of vertical tail, single and twin (with different cant angles) on the flow field and the corresponding aerodynamic forces and moments of a model of a fighter A/C. Aerodynamic forces under different flight conditions and different vertical tail settings were measured in a supersonic wind tunnel. Furthermore, effects of ver...
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Copyright and Moral Rights for the articles on this site are retained by the individual authors and/or other copyright owners. For more information on Open Research Online's data policy on reuse of materials please consult the policies page. Musicians have always been interested in the evolution of their instruments. This evolution might be done either to adapt an instrument's quality to musici...
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A 1/6-scale F-18 wind-tunnel model was tested in the Transonic Dynamics Tunnel at the NASA Langley Research Center as part of the Actively Controlled Response Of Buffet-Affected Tails (ACROBAT) program to assess the use of active controls in reducing vertical tail buffeting. The starboard vertical tail was equipped with an active rudder and other aerodynamic devices, and the port vertical tail ...
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This paper presents an application of the nonlinear optimal control techniques to the design of launch vehicle autopilots. The optimal control is given by the solution to the Hamilton-Jacobi-Bellman (HJB) equation, which in this case cannot be solved explicity. A method based upon Successive Galerkin Approximation (SGA), is used to obtain an approximate optimal solution. Simulation results invo...
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ژورنال
عنوان ژورنال: Journal of Aircraft
سال: 2019
ISSN: 1533-3868
DOI: 10.2514/1.c034907