XFOIL Version 6.96 Calculated polar for: NACA 64A-010 10.0% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.7715 0.06552 0.06374 -0.0317 1.0000 0.0087 -11.250 -0.7985 0.05836 0.05646 -0.0362 1.0000 0.0086 -11.000 -0.8317 0.05190 0.04982 -0.0378 1.0000 0.0085 -10.750 -0.8652 0.04647 0.04417 -0.0360 1.0000 0.0084 -10.500 -0.9074 0.04092 0.03830 -0.0300 1.0000 0.0082 -10.250 -0.9366 0.03485 0.03178 -0.0246 1.0000 0.0082 -10.000 -0.9470 0.03047 0.02698 -0.0205 1.0000 0.0083 -9.750 -0.9461 0.02726 0.02341 -0.0172 1.0000 0.0085 -9.500 -0.9345 0.02560 0.02153 -0.0151 1.0000 0.0088 -9.250 -0.9196 0.02440 0.02016 -0.0133 1.0000 0.0091 -9.000 -0.8998 0.02418 0.01984 -0.0121 1.0000 0.0093 -8.750 -0.8953 0.02042 0.01565 -0.0088 1.0000 0.0096 -8.500 -0.8820 0.01848 0.01353 -0.0066 1.0000 0.0100 -8.250 -0.8639 0.01762 0.01260 -0.0051 1.0000 0.0103 -8.000 -0.8447 0.01700 0.01192 -0.0037 1.0000 0.0107 -7.750 -0.8260 0.01627 0.01112 -0.0022 1.0000 0.0110 -7.500 -0.8070 0.01565 0.01043 -0.0007 1.0000 0.0114 -7.250 -0.7891 0.01489 0.00959 0.0011 1.0000 0.0117 -7.000 -0.7707 0.01430 0.00895 0.0028 1.0000 0.0122 -6.750 -0.7523 0.01381 0.00841 0.0045 1.0000 0.0127 -6.500 -0.7322 0.01354 0.00810 0.0059 0.9999 0.0131 -6.250 -0.7017 0.01229 0.00673 0.0048 0.9977 0.0140 -6.000 -0.6693 0.01149 0.00587 0.0033 0.9951 0.0149 -5.750 -0.6367 0.01106 0.00543 0.0020 0.9920 0.0159 -5.500 -0.6036 0.01062 0.00496 0.0006 0.9888 0.0169 -5.250 -0.5688 0.01025 0.00455 -0.0011 0.9863 0.0181 -5.000 -0.5379 0.00981 0.00406 -0.0020 0.9812 0.0194 -4.750 -0.5046 0.00929 0.00352 -0.0034 0.9773 0.0223 -4.500 -0.4719 0.00900 0.00321 -0.0046 0.9715 0.0248 -4.250 -0.4378 0.00862 0.00283 -0.0061 0.9654 0.0305 -4.000 -0.4059 0.00831 0.00253 -0.0072 0.9557 0.0402 -3.750 -0.3752 0.00793 0.00227 -0.0080 0.9439 0.0681 -3.500 -0.3484 0.00742 0.00199 -0.0080 0.9286 0.1316 -3.250 -0.3261 0.00675 0.00169 -0.0072 0.9114 0.2419 -3.000 -0.3074 0.00591 0.00139 -0.0058 0.8942 0.3953 -2.750 -0.2861 0.00544 0.00124 -0.0046 0.8784 0.5017 -2.500 -0.2618 0.00526 0.00116 -0.0039 0.8641 0.5500 -2.250 -0.2363 0.00516 0.00109 -0.0034 0.8508 0.5795 -2.000 -0.2104 0.00509 0.00104 -0.0029 0.8383 0.6042 -1.750 -0.1848 0.00501 0.00100 -0.0024 0.8262 0.6325 -1.500 -0.1590 0.00495 0.00098 -0.0019 0.8148 0.6587 -1.250 -0.1335 0.00490 0.00096 -0.0014 0.8039 0.6850 -1.000 -0.1071 0.00488 0.00094 -0.0011 0.7933 0.7033 -0.750 -0.0805 0.00486 0.00093 -0.0008 0.7829 0.7184 -0.500 -0.0538 0.00485 0.00093 -0.0005 0.7728 0.7322 -0.250 -0.0271 0.00484 0.00092 -0.0002 0.7628 0.7432 0.000 0.0000 0.00483 0.00092 0.0000 0.7529 0.7529 0.250 0.0272 0.00484 0.00092 0.0002 0.7432 0.7628 0.500 0.0539 0.00485 0.00093 0.0004 0.7322 0.7728 0.750 0.0805 0.00486 0.00093 0.0007 0.7185 0.7829 1.000 0.1071 0.00488 0.00094 0.0010 0.7035 0.7933 1.250 0.1335 0.00490 0.00096 0.0014 0.6846 0.8039 1.500 0.1591 0.00495 0.00098 0.0019 0.6588 0.8148 1.750 0.1848 0.00501 0.00100 0.0024 0.6327 0.8263 2.000 0.2104 0.00509 0.00104 0.0029 0.6040 0.8383 2.250 0.2363 0.00516 0.00110 0.0034 0.5799 0.8508 2.500 0.2618 0.00525 0.00116 0.0039 0.5508 0.8640 2.750 0.2860 0.00545 0.00124 0.0046 0.5010 0.8784 3.000 0.3073 0.00593 0.00139 0.0058 0.3917 0.8942 3.250 0.3261 0.00675 0.00169 0.0072 0.2413 0.9114 3.500 0.3484 0.00741 0.00199 0.0080 0.1329 0.9285 3.750 0.3751 0.00793 0.00227 0.0080 0.0683 0.9439 4.000 0.4058 0.00831 0.00253 0.0072 0.0405 0.9557 4.250 0.4378 0.00862 0.00283 0.0061 0.0303 0.9654 4.500 0.4719 0.00900 0.00321 0.0046 0.0249 0.9714 4.750 0.5046 0.00929 0.00352 0.0034 0.0222 0.9774 5.000 0.5376 0.00986 0.00412 0.0020 0.0191 0.9813 5.250 0.5689 0.01022 0.00452 0.0011 0.0180 0.9863 5.500 0.6036 0.01061 0.00494 -0.0006 0.0169 0.9888 5.750 0.6368 0.01104 0.00540 -0.0020 0.0158 0.9920 6.000 0.6692 0.01151 0.00590 -0.0033 0.0149 0.9951 6.250 0.7015 0.01232 0.00676 -0.0047 0.0140 0.9977 6.500 0.7323 0.01350 0.00806 -0.0059 0.0131 0.9999 6.750 0.7527 0.01378 0.00837 -0.0046 0.0126 1.0000 7.000 0.7704 0.01436 0.00901 -0.0027 0.0122 1.0000 7.250 0.7889 0.01493 0.00964 -0.0010 0.0117 1.0000 7.500 0.8070 0.01566 0.01045 0.0007 0.0113 1.0000 7.750 0.8257 0.01635 0.01121 0.0023 0.0110 1.0000 8.000 0.8443 0.01712 0.01206 0.0038 0.0107 1.0000 8.250 0.8632 0.01781 0.01281 0.0052 0.0104 1.0000 8.500 0.8818 0.01854 0.01359 0.0066 0.0100 1.0000 8.750 0.8964 0.02018 0.01538 0.0086 0.0097 1.0000 9.000 0.8999 0.02415 0.01981 0.0120 0.0093 1.0000 9.250 0.9186 0.02458 0.02037 0.0134 0.0091 1.0000 9.500 0.9344 0.02560 0.02154 0.0151 0.0088 1.0000 9.750 0.9449 0.02746 0.02363 0.0173 0.0086 1.0000 10.000 0.9479 0.03032 0.02681 0.0204 0.0083 1.0000 10.250 0.9377 0.03470 0.03161 0.0245 0.0082 1.0000 10.500 0.9096 0.04068 0.03805 0.0298 0.0082 1.0000 10.750 0.8614 0.04699 0.04471 0.0362 0.0084 1.0000 11.000 0.8303 0.05214 0.05007 0.0377 0.0085 1.0000 11.250 0.8031 0.05765 0.05572 0.0363 0.0086 1.0000 11.500 0.7691 0.06616 0.06439 0.0312 0.0087 1.0000