XFOIL Version 6.96 Calculated polar for: NACA 65(3)-218 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9693 0.10260 0.09971 -0.0483 1.0000 0.0157 -19.500 -0.9885 0.09557 0.09252 -0.0521 1.0000 0.0157 -19.250 -1.0028 0.08957 0.08638 -0.0552 1.0000 0.0158 -19.000 -1.0127 0.08441 0.08110 -0.0579 1.0000 0.0159 -18.750 -1.0188 0.07997 0.07654 -0.0601 1.0000 0.0160 -18.500 -1.0261 0.07549 0.07194 -0.0623 1.0000 0.0161 -18.250 -1.0320 0.07151 0.06784 -0.0638 1.0000 0.0161 -18.000 -1.0478 0.06649 0.06264 -0.0651 1.0000 0.0162 -17.750 -1.0561 0.06263 0.05866 -0.0657 1.0000 0.0165 -17.500 -1.0574 0.05965 0.05561 -0.0663 1.0000 0.0166 -17.250 -1.0562 0.05698 0.05287 -0.0668 1.0000 0.0167 -17.000 -1.0531 0.05457 0.05040 -0.0672 1.0000 0.0168 -16.750 -1.0507 0.05216 0.04791 -0.0675 1.0000 0.0169 -16.500 -1.0457 0.05006 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0.6123 0.6646 2.750 0.4944 0.00699 0.00223 -0.0441 0.6080 0.6677 3.000 0.5231 0.00707 0.00229 -0.0445 0.6033 0.6707 3.250 0.5519 0.00704 0.00231 -0.0448 0.5981 0.6737 3.500 0.5800 0.00706 0.00231 -0.0449 0.5895 0.6766 3.750 0.6083 0.00705 0.00234 -0.0452 0.5812 0.6799 4.000 0.6356 0.00709 0.00238 -0.0452 0.5714 0.6835 4.250 0.6639 0.00710 0.00243 -0.0454 0.5609 0.6871 4.500 0.6914 0.00717 0.00250 -0.0456 0.5499 0.6907 4.750 0.7185 0.00727 0.00257 -0.0456 0.5360 0.6940 5.000 0.7451 0.00736 0.00266 -0.0455 0.5199 0.6977 5.250 0.7703 0.00752 0.00279 -0.0452 0.4957 0.7016 5.500 0.7900 0.00795 0.00302 -0.0440 0.4456 0.7056 5.750 0.7997 0.00890 0.00355 -0.0412 0.3586 0.7096 6.000 0.8080 0.00984 0.00412 -0.0382 0.2832 0.7137 6.250 0.8161 0.01064 0.00466 -0.0351 0.2210 0.7186 6.500 0.8225 0.01141 0.00519 -0.0317 0.1701 0.7234 6.750 0.8241 0.01208 0.00567 -0.0274 0.1304 0.7282 7.000 0.8257 0.01286 0.00629 -0.0233 0.0949 0.7334 7.250 0.8284 0.01369 0.00700 -0.0196 0.0656 0.7388 7.500 0.8351 0.01448 0.00768 -0.0167 0.0459 0.7443 7.750 0.8467 0.01512 0.00829 -0.0147 0.0382 0.7495 8.000 0.8591 0.01573 0.00893 -0.0128 0.0340 0.7554 8.250 0.8734 0.01631 0.00953 -0.0113 0.0318 0.7616 8.500 0.8850 0.01704 0.01028 -0.0095 0.0293 0.7677 8.750 0.9003 0.01760 0.01090 -0.0082 0.0282 0.7741 9.000 0.9149 0.01823 0.01157 -0.0069 0.0272 0.7808 9.250 0.9275 0.01897 0.01234 -0.0054 0.0259 0.7873 9.500 0.9374 0.01989 0.01332 -0.0036 0.0246 0.7947 9.750 0.9514 0.02061 0.01409 -0.0024 0.0242 0.8017 10.000 0.9655 0.02132 0.01487 -0.0013 0.0235 0.8095 10.500 0.9913 0.02294 0.01659 0.0012 0.0220 0.8267 10.750 1.0016 0.02394 0.01764 0.0026 0.0214 0.8360 11.000 1.0069 0.02525 0.01904 0.0044 0.0207 0.8466 11.250 1.0186 0.02616 0.02004 0.0055 0.0205 0.8573 11.500 1.0310 0.02705 0.02100 0.0066 0.0201 0.8693 11.750 1.0408 0.02808 0.02213 0.0080 0.0199 0.8840 12.000 1.0519 0.02897 0.02312 0.0092 0.0193 0.9022 12.250 1.0593 0.03007 0.02434 0.0108 0.0191 0.9315 12.500 1.0875 0.03124 0.02563 0.0081 0.0185 0.9758 12.750 1.0959 0.03251 0.02693 0.0092 0.0183 1.0000 13.000 1.1054 0.03393 0.02837 0.0098 0.0180 1.0000 13.250 1.1111 0.03568 0.03015 0.0107 0.0176 1.0000 13.500 1.1139 0.03769 0.03222 0.0116 0.0173 1.0000 13.750 1.1214 0.03937 0.03395 0.0122 0.0171 1.0000 14.000 1.1339 0.04066 0.03529 0.0125 0.0169 1.0000 14.250 1.1426 0.04229 0.03697 0.0129 0.0169 1.0000 14.500 1.1536 0.04376 0.03849 0.0132 0.0166 1.0000 14.750 1.1626 0.04544 0.04022 0.0134 0.0164 1.0000 15.000 1.1734 0.04697 0.04180 0.0136 0.0161 1.0000 15.250 1.1804 0.04888 0.04377 0.0138 0.0159 1.0000 15.500 1.1897 0.05062 0.04555 0.0139 0.0157 1.0000 15.750 1.1973 0.05255 0.04754 0.0139 0.0155 1.0000 16.000 1.2055 0.05447 0.04950 0.0138 0.0153 1.0000 16.250 1.2118 0.05660 0.05168 0.0138 0.0152 1.0000 16.500 1.2175 0.05880 0.05395 0.0137 0.0151 1.0000 16.750 1.2237 0.06102 0.05622 0.0135 0.0150 1.0000 17.000 1.2284 0.06345 0.05869 0.0132 0.0148 1.0000 17.250 1.2332 0.06590 0.06119 0.0129 0.0146 1.0000 17.500 1.2350 0.06870 0.06405 0.0126 0.0144 1.0000 17.750 1.2368 0.07148 0.06691 0.0123 0.0143 1.0000 18.000 1.2365 0.07461 0.07014 0.0119 0.0141 1.0000 18.250 1.2398 0.07745 0.07306 0.0113 0.0141 1.0000 18.500 1.2417 0.08058 0.07629 0.0103 0.0140 1.0000 18.750 1.2424 0.08399 0.07981 0.0091 0.0139 1.0000 19.000 1.2436 0.08727 0.08318 0.0079 0.0138 1.0000 19.250 1.2423 0.09104 0.08706 0.0065 0.0137 1.0000