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Experimental Investigation of Flow Past a Delta Wing Model in Presence of a Canard in Supersonic Regime

Dehghani, Parham | 2016

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  1. Type of Document: M.Sc. Thesis
  2. Language: Farsi
  3. Document No: 49727 (45)
  4. University: Sharif University of Technology
  5. Department: Aerospace Engineering
  6. Advisor(s): Soltani, Mohammad Reza
  7. Abstract:
  8. Application of canard next to the wing have been widely used in military industry for decades. Although it’s most application is in supersonic flying objects, It has to do it’s duty in lower air speeds too. The aim of this study was to investigate the influence on the wing due to the presence of canard in supersonic flow regime. But because of the importance of the issue, significant attempts has been conducted in subsonic flow regime. High research volume, Absence of a comprehensive theory in this branch and the local defense industry demand as a developing country on the other hand, delivers the importance and applicability of the subject. Another issue of importance is that the installation of canard upstream of the wing resulted in some improvements in flow characteristics passing the wing. In the present study, steady and supersonic flow on a delta wing under the influence of adjacent canard (in the form of a half body) is studied experimentally in a wind tunnel. Pressure sensors on the surface of the wing are used to do the experiments and the test data for the present study is pressure distribution on the upper surface of the wing. The effects of the wings and canards angle of attack, as well as flow Mach number on the wing surface flow (pressure distribution) constitutes the final results. The results illustrate that the downwash coming from canard increases the pressure coefficients of the areas near the apex of the wing but decreases as moving towards the trailing edge (compared to the canard-off case). Also increment of the angle of attack of the canard causes the pressure coefficients of the wing surface to grow generally however in some cases different results has been obtained. The outcome of the Mach number growth is the enhancement of the pressure coefficients of the wing. The results can be used to improve the flow of the similar geometries in future studies and could also be used to validate numerical simulations
  9. Keywords:
  10. Delta Wing ; Pressure Distribution ; Wind Tunnel ; Vortex Flow (Eddy Current) ; Supersonic Flow ; Canard Configuration

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