{'fraction_non_alphanumeric': 0.01706036745406824, 'fraction_numerical': 0.003937007874015748, 'mean_word_length': 5.305785123966942, 'pattern_counts': {'":': 0, '<': 0, '<?xml version=': 0, '>': 0, 'https://': 0, 'lorem ipsum': 0, 'www.': 0, 'xml': 0}, 'pii_count': 0, 'substrings_counts': 0, 'word_list_counts': {'cursed_substrings.json': 0, 'profanity_word_list.json': 0, 'sexual_word_list.json': 0, 'zh_pornsignals.json': 0}}
A Study on Airfoil Design for Future Mars Airplane

An optimum airfoil design for future Mars airplane for Mars exploration is obtained by evolutionary computation coupled with a two-dimensional Reynolds-averaged Navier-Stokes solver. The optimized airfoil design is also compared with other airfoil designs optimized at different Reynolds number or at different Mach number to discuss Reynolds number and Mach number effects on airfoil design. The present results indicate 1) optimum airfoil shape in the sense of maximization of lift-to-drag has thin thickness distribution, 2) Optimum camber distribution depends on both Reynolds number and Mach number of the design condition, 3) Optimum leading edge shape depends on Reynolds number of the design condition.