XFOIL Version 6.96 Calculated polar for: NACA 66 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.250 -0.9734 0.09624 0.09379 -0.0536 1.0000 0.0092 -19.000 -1.0111 0.08497 0.08233 -0.0604 0.9805 0.0093 -18.750 -1.0376 0.07472 0.07184 -0.0683 0.9631 0.0092 -18.500 -1.0503 0.06753 0.06442 -0.0740 0.9426 0.0092 -18.250 -1.0649 0.06202 0.05870 -0.0766 0.9227 0.0093 -18.000 -1.0732 0.05790 0.05440 -0.0781 0.9089 0.0093 -17.750 -1.0885 0.05316 0.04946 -0.0794 0.8978 0.0093 -17.500 -1.0933 0.04993 0.04607 -0.0800 0.8880 0.0094 -17.250 -1.0976 0.04693 0.04291 -0.0803 0.8800 0.0094 -17.000 -1.0962 0.04465 0.04050 -0.0802 0.8720 0.0095 -16.750 -1.1004 0.04193 0.03762 -0.0799 0.8654 0.0095 -16.500 -1.0972 0.03999 0.03556 -0.0795 0.8588 0.0096 -16.250 -1.0972 0.03789 0.03332 -0.0788 0.8528 0.0097 -16.000 -1.0990 0.03568 0.03099 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0.7392 0.0221 -5.750 -0.4222 0.01126 0.00443 -0.0378 0.7378 0.0226 -5.500 -0.3977 0.01108 0.00423 -0.0375 0.7365 0.0232 -5.250 -0.3741 0.01083 0.00398 -0.0370 0.7356 0.0242 -5.000 -0.3497 0.01061 0.00377 -0.0366 0.7347 0.0252 -4.750 -0.3248 0.01043 0.00359 -0.0363 0.7337 0.0262 -4.500 -0.2995 0.01026 0.00342 -0.0361 0.7328 0.0273 -4.250 -0.2738 0.01011 0.00326 -0.0359 0.7318 0.0282 -4.000 -0.2484 0.00993 0.00309 -0.0357 0.7308 0.0302 -3.750 -0.2228 0.00977 0.00295 -0.0356 0.7298 0.0326 -3.500 -0.1969 0.00962 0.00282 -0.0355 0.7288 0.0362 -3.250 -0.1715 0.00943 0.00268 -0.0353 0.7279 0.0455 -3.000 -0.1480 0.00913 0.00251 -0.0348 0.7269 0.0805 -2.750 -0.1262 0.00871 0.00233 -0.0340 0.7259 0.1427 -2.500 -0.1048 0.00826 0.00215 -0.0332 0.7250 0.2171 -2.250 -0.0877 0.00752 0.00190 -0.0317 0.7239 0.3479 -2.000 -0.0710 0.00673 0.00163 -0.0302 0.7227 0.4911 -1.750 -0.0545 0.00596 0.00145 -0.0284 0.7189 0.6508 -1.500 -0.0274 0.00586 0.00142 -0.0283 0.7109 0.6838 -1.250 0.0000 0.00585 0.00140 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0.4262 0.01114 0.00405 -0.0091 0.0162 0.7634 4.000 0.4472 0.01135 0.00426 -0.0082 0.0161 0.7652 4.250 0.4680 0.01156 0.00449 -0.0073 0.0161 0.7673 4.500 0.4888 0.01179 0.00472 -0.0063 0.0161 0.7695 4.750 0.5095 0.01202 0.00497 -0.0054 0.0160 0.7719 5.000 0.5301 0.01228 0.00523 -0.0045 0.0160 0.7745 5.250 0.5506 0.01255 0.00551 -0.0035 0.0160 0.7773 5.500 0.5710 0.01283 0.00579 -0.0026 0.0160 0.7798 5.750 0.5913 0.01313 0.00610 -0.0017 0.0160 0.7821 6.000 0.6112 0.01342 0.00641 -0.0008 0.0160 0.7847 6.250 0.6309 0.01374 0.00675 0.0002 0.0160 0.7875 6.500 0.6502 0.01409 0.00712 0.0012 0.0158 0.7905 6.750 0.6698 0.01444 0.00749 0.0022 0.0157 0.7936 7.000 0.6884 0.01484 0.00790 0.0032 0.0155 0.7965 7.250 0.7073 0.01523 0.00832 0.0042 0.0156 0.7994 7.500 0.7261 0.01562 0.00875 0.0052 0.0154 0.8027 7.750 0.7444 0.01604 0.00920 0.0063 0.0151 0.8063 8.000 0.7626 0.01648 0.00967 0.0073 0.0150 0.8100 8.250 0.7808 0.01694 0.01015 0.0083 0.0149 0.8134 8.500 0.7984 0.01743 0.01068 0.0093 0.0148 0.8170 8.750 0.8153 0.01794 0.01123 0.0105 0.0146 0.8211 9.000 0.8322 0.01847 0.01180 0.0116 0.0144 0.8254 9.250 0.8488 0.01904 0.01240 0.0127 0.0143 0.8296 9.500 0.8649 0.01963 0.01304 0.0138 0.0142 0.8339 9.750 0.8795 0.02030 0.01375 0.0151 0.0139 0.8392 10.000 0.8940 0.02100 0.01449 0.0164 0.0138 0.8448 10.250 0.9058 0.02188 0.01541 0.0180 0.0135 0.8501 10.500 0.9180 0.02273 0.01633 0.0195 0.0133 0.8563 10.750 0.9309 0.02357 0.01723 0.0208 0.0131 0.8626 11.000 0.9468 0.02419 0.01792 0.0218 0.0130 0.8688 11.250 0.9626 0.02482 0.01863 0.0228 0.0128 0.8762 11.500 0.9769 0.02557 0.01944 0.0238 0.0127 0.8838 11.750 0.9904 0.02634 0.02030 0.0251 0.0125 0.8931 12.000 1.0035 0.02714 0.02119 0.0263 0.0123 0.9032 12.250 1.0161 0.02798 0.02211 0.0275 0.0121 0.9158 12.500 1.0286 0.02882 0.02306 0.0287 0.0118 0.9335 12.750 1.0467 0.02986 0.02421 0.0285 0.0117 0.9576 13.000 1.0725 0.03108 0.02551 0.0263 0.0115 0.9830 13.500 1.0945 0.03335 0.02784 0.0282 0.0112 1.0000 13.750 1.1043 0.03467 0.02917 0.0292 0.0110 1.0000 14.000 1.1131 0.03613 0.03066 0.0302 0.0108 1.0000 14.250 1.1251 0.03723 0.03186 0.0308 0.0107 1.0000 14.500 1.1356 0.03855 0.03326 0.0315 0.0107 1.0000 14.750 1.1464 0.03983 0.03464 0.0321 0.0105 1.0000 15.000 1.1563 0.04123 0.03614 0.0326 0.0103 1.0000 15.250 1.1632 0.04294 0.03792 0.0333 0.0103 1.0000 15.500 1.1719 0.04451 0.03960 0.0338 0.0100 1.0000 15.750 1.1776 0.04642 0.04162 0.0344 0.0098 1.0000 16.000 1.1833 0.04837 0.04365 0.0348 0.0098 1.0000 16.250 1.1883 0.05043 0.04581 0.0351 0.0096 1.0000 16.500 1.1913 0.05277 0.04825 0.0354 0.0095 1.0000 16.750 1.1959 0.05496 0.05053 0.0354 0.0094 1.0000 17.000 1.1977 0.05758 0.05325 0.0354 0.0093 1.0000 17.250 1.1982 0.06043 0.05620 0.0352 0.0093 1.0000 17.500 1.1990 0.06332 0.05919 0.0348 0.0092 1.0000 17.750 1.2005 0.06621 0.06216 0.0342 0.0091 1.0000 18.000 1.1975 0.06980 0.06586 0.0334 0.0090 1.0000 18.250 1.1962 0.07329 0.06945 0.0324 0.0090 1.0000 18.500 1.1933 0.07712 0.07338 0.0311 0.0089 1.0000 18.750 1.1867 0.08161 0.07799 0.0294 0.0089 1.0000 19.000 1.1816 0.08602 0.08251 0.0276 0.0089 1.0000 19.250 1.1729 0.09116 0.08778 0.0253 0.0089 1.0000