Jeong S, Chiba K, Obayashi S (2005) Data mining for aerodynamic design space. Proc Inst Mech Eng Part G J Aerosp Eng 225:469–479 Jeong S, Shimoyama K (2011) Review of data mining for multi-disciplinary design optimization. Koning WJF, Romander EA, Johnson W (2020) Optimization of low Reynolds number airfoils for Martian rotor applications using an evolutionary algorithm. Ĭastelli MR, Garbo F, Benini E (2011) Numerical investigation of laminar to turbulent boundary layer transition on a Naca 0012 airfoil for vertical-axis wind turbine applications. In: 40th fluid dynamics conference exhibition. J Aircr 51:1864–1872Īnyoji M, Nose K, Ida S, Numata D, Nagai H, Asai K (2010) Low Reynolds number airfoil testing in a Mars wind tunnel. In: 44th AIAA aerospace science meet exhibition, vol 23, pp 17793–17800Īnyoji M, Nonomura T, Aono H, Oyama A, Fujii K, Nagai H, Asai K (2014) Computational and experimental analysis of a high-performance airfoil under low-Reynolds-number flow condition. Oyama A, Fujii K (2006) A study on airfoil design for future mars airplane. In: 2nd AIAA ‘Unmanned Unlimited’ conference work exhibitions. Smith S, Guynn M, Streett C, Beeler G (2003) Mars airplane airfoil design with application to ARES. Laitone EV (1997) Wind tunnel tests of wings at Reynolds numbers below 70 000. Ladson CL (1988) Effects of independent variation of Mach and Reynolds numbers on the low-speed aerodynamic characteristics of the NACA0012 airfoil section. Jung J, Yee K, Misaka T, Jeong S (2017) Low Reynolds number airfoil design for a Mars exploration airplane using a transition model. Trans Jpn Soc Aeron Space Sci Aerosp Technol Jpn 10:Te_5–Te_10 J Spacecr Rockets 43:1026–1034įujita K, Luong R, Nagai H, Asai K (2012) Conceptual design of mars airplane. īraun RD, Wright HS, Croom MA, Levine JS, Spencer DA (2006) Design of the ARES mars airplane and mission architecture. įujita K, Karaca H, Nagai H (2020) Parametric study of Mars helicopter for pit crater exploration. O’Brien P (2003) Using a robotic helicopter to fuel interest in and augment the human exploration of the planet Mars. Accelator space commercial exploration new discovery conference ASCEND 2020, pp 1–19ĭatta A, Roget B, Griffiths D, Pugliese G, Sitaraman J, Bao J, Liu L, Gamard O (2003) Design of a martian autonomous rotary-wing vehicle. Withrow-Maser S, Johnson W, Young L, Koning W, Kuang W, Malpica C, Balaram J, Tzanetos T (2020) Mars science helicopter: conceptual design of the next generation of mars rotorcraft. Quantitative and qualitative correlations between the design variables and airfoil performance are also analyzed using analysis of variance and self-organizing map methods to extract the geometric features that affect airfoil performance. Results demonstrate improvements in the power consumption and efficiency of the propeller using the designed airfoil over those of the propellers using reference airfoils. Then, the performance and efficiency of the propeller are investigated. The Adkins method is used to determine the optimal shape of the propeller using the designed airfoil. A multi-objective genetic algorithm is used to determine the optimal airfoil shape, and a Kriging model is used to reduce the computation time. Furthermore, multi-objective shape optimization is performed using a shape-definition method with a high degree of freedom to enable the inclusion of a variety of airfoil shapes. To increase the accuracy of performance evaluation in the low-Reynolds-number and high-subsonic flows condition on Mars, a Reynolds-averaged Navier–Stokes simulation using the γ-Re θ transition model, which can predict the laminar separation bubble and the location of the laminar–turbulent transition with high accuracy, is employed. This study aims to improve the aerodynamic performance of a propeller for Mars exploration aircraft by applying multi-objective shape optimization to its airfoils.
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