XFOIL Version 6.96 Calculated polar for: SD6060-104-88 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.4864 0.08693 0.08477 -0.0258 1.0000 0.0182 -9.250 -0.4870 0.08278 0.08064 -0.0281 1.0000 0.0185 -9.000 -0.4900 0.07810 0.07599 -0.0311 1.0000 0.0190 -6.500 -0.4699 0.02021 0.01497 -0.0476 0.9571 0.0120 -6.250 -0.4491 0.01824 0.01271 -0.0462 0.9462 0.0121 -6.000 -0.4276 0.01672 0.01097 -0.0449 0.9364 0.0121 -5.750 -0.4066 0.01539 0.00951 -0.0436 0.9274 0.0127 -5.500 -0.3844 0.01450 0.00850 -0.0424 0.9177 0.0131 -5.250 -0.3614 0.01377 0.00768 -0.0414 0.9087 0.0138 -5.000 -0.3380 0.01326 0.00709 -0.0404 0.9006 0.0148 -4.750 -0.3138 0.01266 0.00640 -0.0396 0.8912 0.0157 -4.500 -0.2901 0.01202 0.00565 -0.0386 0.8829 0.0163 -4.250 -0.2675 0.01112 0.00462 -0.0375 0.8742 0.0178 -4.000 -0.2425 0.01063 0.00407 -0.0368 0.8655 0.0208 -3.750 -0.2178 0.01011 0.00348 -0.0360 0.8577 0.0313 -3.500 -0.1934 0.00948 0.00309 -0.0355 0.8485 0.0821 -3.250 -0.1685 0.00905 0.00283 -0.0351 0.8406 0.1360 -3.000 -0.1439 0.00854 0.00259 -0.0347 0.8318 0.2137 -2.750 -0.1211 0.00778 0.00237 -0.0341 0.8232 0.3579 -2.500 -0.0989 0.00709 0.00219 -0.0333 0.8152 0.5096 -2.250 -0.0755 0.00663 0.00210 -0.0324 0.8061 0.6240 -2.000 -0.0511 0.00640 0.00205 -0.0316 0.7981 0.6990 -1.750 -0.0257 0.00627 0.00202 -0.0308 0.7893 0.7502 -1.500 0.0003 0.00621 0.00200 -0.0302 0.7809 0.7859 -1.250 0.0263 0.00618 0.00197 -0.0295 0.7728 0.8143 -1.000 0.0525 0.00616 0.00196 -0.0289 0.7637 0.8382 -0.750 0.0785 0.00618 0.00195 -0.0282 0.7556 0.8581 -0.500 0.1044 0.00619 0.00196 -0.0275 0.7465 0.8758 -0.250 0.1300 0.00622 0.00196 -0.0268 0.7376 0.8926 0.000 0.1554 0.00627 0.00196 -0.0259 0.7292 0.9077 0.250 0.1808 0.00629 0.00199 -0.0251 0.7197 0.9217 0.500 0.2065 0.00635 0.00201 -0.0244 0.7111 0.9351 0.750 0.2336 0.00640 0.00202 -0.0239 0.7021 0.9469 1.000 0.2624 0.00645 0.00204 -0.0239 0.6927 0.9576 1.250 0.2968 0.00652 0.00206 -0.0252 0.6835 0.9644 1.500 0.3302 0.00658 0.00208 -0.0263 0.6736 0.9714 1.750 0.3691 0.00664 0.00210 -0.0287 0.6628 0.9748 2.000 0.4069 0.00669 0.00212 -0.0309 0.6520 0.9786 2.250 0.4418 0.00676 0.00215 -0.0325 0.6408 0.9835 2.500 0.4807 0.00681 0.00216 -0.0350 0.6286 0.9862 2.750 0.5182 0.00686 0.00218 -0.0372 0.6156 0.9898 3.000 0.5540 0.00693 0.00223 -0.0390 0.6016 0.9939 3.250 0.5914 0.00698 0.00226 -0.0413 0.5867 0.9972 3.500 0.6261 0.00703 0.00230 -0.0429 0.5701 1.0000 3.750 0.6480 0.00711 0.00236 -0.0419 0.5538 1.0000 4.000 0.6697 0.00721 0.00244 -0.0409 0.5351 1.0000 4.250 0.6911 0.00735 0.00253 -0.0397 0.5142 1.0000 4.500 0.7123 0.00753 0.00265 -0.0386 0.4889 1.0000 4.750 0.7329 0.00777 0.00279 -0.0373 0.4576 1.0000 5.000 0.7527 0.00811 0.00299 -0.0360 0.4172 1.0000 5.250 0.7725 0.00851 0.00322 -0.0346 0.3752 1.0000 5.500 0.7927 0.00892 0.00348 -0.0334 0.3370 1.0000 5.750 0.8124 0.00942 0.00379 -0.0322 0.2927 1.0000 6.000 0.8323 0.00997 0.00414 -0.0311 0.2491 1.0000 6.250 0.8535 0.01045 0.00449 -0.0301 0.2148 1.0000 6.500 0.8747 0.01097 0.00486 -0.0292 0.1810 1.0000 7.000 0.9169 0.01209 0.00571 -0.0275 0.1202 1.0000 7.250 0.9366 0.01280 0.00624 -0.0265 0.0853 1.0000 7.500 0.9522 0.01391 0.00703 -0.0249 0.0388 1.0000 7.750 0.9709 0.01475 0.00783 -0.0236 0.0264 1.0000 8.000 0.9913 0.01538 0.00851 -0.0225 0.0232 1.0000 8.250 1.0083 0.01632 0.00952 -0.0210 0.0202 1.0000 8.500 1.0271 0.01703 0.01031 -0.0197 0.0191 1.0000 8.750 1.0451 0.01778 0.01116 -0.0184 0.0179 1.0000 9.000 1.0618 0.01859 0.01206 -0.0169 0.0170 1.0000 9.250 1.0772 0.01946 0.01300 -0.0153 0.0160 1.0000 9.500 1.0889 0.02056 0.01415 -0.0133 0.0148 1.0000 9.750 1.0873 0.02257 0.01631 -0.0093 0.0138 1.0000 10.000 1.1000 0.02340 0.01723 -0.0074 0.0134 1.0000 10.250 1.1108 0.02446 0.01839 -0.0053 0.0129 1.0000 10.500 1.1208 0.02566 0.01971 -0.0033 0.0124 1.0000 10.750 1.1303 0.02700 0.02115 -0.0014 0.0120 1.0000 11.000 1.1399 0.02824 0.02250 0.0002 0.0114 1.0000 11.250 1.1481 0.02962 0.02397 0.0018 0.0108 1.0000 11.500 1.1547 0.03121 0.02563 0.0033 0.0103 1.0000 11.750 1.1569 0.03378 0.02831 0.0050 0.0097 1.0000 12.000 1.1559 0.03715 0.03193 0.0068 0.0093 1.0000 12.250 1.1591 0.03885 0.03380 0.0080 0.0091 1.0000 12.500 1.1599 0.04121 0.03634 0.0091 0.0090 1.0000 12.750 1.1593 0.04366 0.03898 0.0100 0.0088 1.0000 13.000 1.1574 0.04630 0.04180 0.0105 0.0084 1.0000 13.250 1.1501 0.04993 0.04564 0.0107 0.0085 1.0000 13.500 1.1420 0.05370 0.04960 0.0105 0.0083 1.0000 13.750 1.1298 0.05825 0.05436 0.0097 0.0083 1.0000 14.000 1.1196 0.06263 0.05892 0.0084 0.0081 1.0000 14.250 1.1064 0.06775 0.06423 0.0065 0.0081 1.0000 14.500 1.0896 0.07387 0.07054 0.0037 0.0081 1.0000 14.750 1.0729 0.08041 0.07726 0.0003 0.0081 1.0000 15.000 1.0518 0.08843 0.08547 -0.0042 0.0083 1.0000 15.250 1.0343 0.09627 0.09347 -0.0090 0.0082 1.0000 15.500 1.0100 0.10632 0.10369 -0.0153 0.0084 1.0000 15.750 0.9887 0.11635 0.11386 -0.0215 0.0086 1.0000 16.000 0.9656 0.12745 0.12510 -0.0284 0.0087 1.0000 16.250 0.9376 0.14058 0.13833 -0.0361 0.0091 1.0000