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The application of suction and blowing in performance improvement of transonic airfoils with shock control bump

Mazaheri, K ; Sharif University of Technology | 2017

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  1. Type of Document: Article
  2. DOI: 10.24200/sci.2017.4032
  3. Publisher: Sharif University of Technology , 2017
  4. Abstract:
  5. Shock Control Bump (SCB) reduces the wave drag in transonic ight. To control the boundary layer separation and to reduce the wave drag for two transonic airfoils, RAE-2822 and NACA-64A010, we investigate the application of two flow control methods, i.e. suction and blowing, to add them to the SCB. An adjoint gradient-based optimization algorithm is used to find the optimum shape and location of SCB. The performance of both Hybrid Suction/SCB (HSS) and Hybrid Blowing/SCB (HBS) is a function of the sucked or injected mass flow rate and their position. A parametric study is performed to find the near optimum values of the aerodynamic coefficients and efficiency. A RANS solver is validated and used for this flow analysis. Using HSS method, the aerodynamic efficiencies of these two airfoils are increased by, respectively, 8.6% and 3.9%, in comparison to the airfoils with optimized bumps. For HBS configuration, improvements are respectively 13.5% and 9.0%. The best non-dimensional mass flow rate for suction is found to be around 0.003 for both airfoils, and for blowing this is about 0.0025 for RAE-2822 airfoil and about 0.002 for NACA-64A010. The best locations for suction and blowing are found to be, respectively, right before and after the SCB. © 2017 Sharif University of Technology. All rights reserved
  6. Keywords:
  7. Adjoint optimization ; Blowing ; Drag reduction ; Hybrid flow control tools ; Shock control bump ; Shock wave ; Suction ; Transonic airfoil ; Aerodynamics ; Blow molding ; Boundary layers ; Drag ; Efficiency ; Flow control ; Mass transfer ; Optimization ; Shock absorbers ; Shock waves ; Transonic aerodynamics ; Adjoint optimizations ; Hybrid flow ; Shock control ; Transonic airfoils ; Airfoils ; Algorithm ; Boundary layer ; Control system ; Performance assessment
  8. Source: Scientia Iranica ; Volume 24, Issue 1 , 2017 , Pages 274-292 ; 10263098 (ISSN)
  9. URL: http://scientiairanica.sharif.edu/article_4032.html