XFOIL Version 6.96 Calculated polar for: ARA-D 13% AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -15.250 -1.0089 0.08305 0.08040 -0.0206 1.0000 0.0150 -15.000 -1.1308 0.05621 0.05322 -0.0407 1.0000 0.0146 -14.750 -1.1697 0.04112 0.03770 -0.0561 1.0000 0.0144 -14.500 -1.1865 0.03754 0.03394 -0.0546 1.0000 0.0145 -14.250 -1.1938 0.03415 0.03033 -0.0533 1.0000 0.0146 -14.000 -1.1896 0.03153 0.02755 -0.0523 1.0000 0.0147 -13.750 -1.1778 0.02958 0.02546 -0.0514 1.0000 0.0149 -13.500 -1.1614 0.02805 0.02383 -0.0508 1.0000 0.0150 -13.250 -1.1423 0.02678 0.02246 -0.0502 1.0000 0.0152 -13.000 -1.1214 0.02566 0.02127 -0.0498 1.0000 0.0154 -12.750 -1.0993 0.02465 0.02017 -0.0494 1.0000 0.0155 -12.500 -1.0763 0.02369 0.01914 -0.0490 1.0000 0.0157 -12.250 -1.0526 0.02280 0.01816 -0.0487 1.0000 0.0159 -12.000 -1.0282 0.02195 0.01724 -0.0484 1.0000 0.0161 -11.750 -1.0033 0.02115 0.01636 -0.0482 1.0000 0.0164 -11.500 -0.9778 0.02040 0.01553 -0.0480 1.0000 0.0166 -11.250 -0.9518 0.01969 0.01474 -0.0478 1.0000 0.0168 -11.000 -0.9252 0.01907 0.01405 -0.0477 1.0000 0.0170 -10.750 -0.8992 0.01824 0.01313 -0.0475 1.0000 0.0173 -10.500 -0.8732 0.01737 0.01222 -0.0474 1.0000 0.0178 -10.250 -0.8459 0.01678 0.01159 -0.0474 1.0000 0.0181 -10.000 -0.8181 0.01627 0.01105 -0.0474 1.0000 0.0186 -9.750 -0.7900 0.01579 0.01053 -0.0474 1.0000 0.0190 -9.500 -0.7618 0.01533 0.01003 -0.0474 1.0000 0.0195 -9.250 -0.7333 0.01492 0.00957 -0.0474 1.0000 0.0199 -9.000 -0.7053 0.01431 0.00892 -0.0474 1.0000 0.0206 -8.750 -0.6768 0.01385 0.00846 -0.0475 1.0000 0.0213 -8.500 -0.6480 0.01349 0.00808 -0.0476 1.0000 0.0221 -8.250 -0.6185 0.01317 0.00774 -0.0478 0.9982 0.0230 -8.000 -0.5839 0.01272 0.00728 -0.0492 0.9832 0.0243 -7.750 -0.5522 0.01247 0.00701 -0.0497 0.9640 0.0256 -7.500 -0.5252 0.01228 0.00674 -0.0491 0.9407 0.0268 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0.1046 -2.000 0.1171 0.00948 0.00302 -0.0492 0.5872 0.1136 -1.750 0.1471 0.00945 0.00297 -0.0494 0.5732 0.1222 -1.500 0.1771 0.00944 0.00293 -0.0497 0.5593 0.1307 -1.250 0.2071 0.00939 0.00289 -0.0499 0.5461 0.1416 -1.000 0.2371 0.00938 0.00285 -0.0502 0.5319 0.1517 -0.750 0.2670 0.00939 0.00283 -0.0504 0.5174 0.1627 -0.500 0.2970 0.00937 0.00282 -0.0507 0.5032 0.1774 -0.250 0.3270 0.00935 0.00281 -0.0510 0.4890 0.1949 0.000 0.3569 0.00933 0.00281 -0.0513 0.4735 0.2194 0.250 0.3867 0.00927 0.00281 -0.0516 0.4578 0.2597 0.500 0.4165 0.00904 0.00283 -0.0521 0.4425 0.3617 0.750 0.4455 0.00843 0.00288 -0.0527 0.4264 0.6093 1.250 0.4916 0.00767 0.00298 -0.0498 0.3924 0.9531 1.500 0.5251 0.00763 0.00286 -0.0508 0.3734 1.0000 1.750 0.5547 0.00781 0.00293 -0.0511 0.3546 1.0000 2.000 0.5842 0.00801 0.00301 -0.0513 0.3351 1.0000 2.250 0.6137 0.00822 0.00310 -0.0516 0.3170 1.0000 2.500 0.6432 0.00842 0.00320 -0.0519 0.3014 1.0000 2.750 0.6726 0.00863 0.00331 -0.0521 0.2868 1.0000 3.250 0.7314 0.00903 0.00354 -0.0527 0.2618 1.0000 3.500 0.7607 0.00923 0.00367 -0.0529 0.2517 1.0000 3.750 0.7900 0.00943 0.00380 -0.0532 0.2416 1.0000 4.000 0.8193 0.00961 0.00394 -0.0534 0.2330 1.0000 4.250 0.8484 0.00984 0.00408 -0.0537 0.2241 1.0000 4.500 0.8776 0.01001 0.00422 -0.0539 0.2174 1.0000 4.750 0.9065 0.01023 0.00438 -0.0542 0.2097 1.0000 5.000 0.9356 0.01042 0.00454 -0.0544 0.2037 1.0000 5.250 0.9645 0.01061 0.00469 -0.0546 0.1978 1.0000 5.500 0.9930 0.01087 0.00489 -0.0548 0.1909 1.0000 5.750 1.0220 0.01103 0.00504 -0.0550 0.1871 1.0000 6.000 1.0506 0.01124 0.00522 -0.0552 0.1824 1.0000 6.250 1.0788 0.01152 0.00545 -0.0554 0.1766 1.0000 6.500 1.1075 0.01168 0.00562 -0.0556 0.1736 1.0000 6.750 1.1359 0.01189 0.00581 -0.0557 0.1696 1.0000 7.000 1.1638 0.01215 0.00603 -0.0559 0.1653 1.0000 7.250 1.1916 0.01241 0.00628 -0.0560 0.1614 1.0000 7.500 1.2199 0.01260 0.00647 -0.0561 0.1586 1.0000 7.750 1.2477 0.01283 0.00669 -0.0562 0.1551 1.0000 8.000 1.2749 0.01313 0.00696 -0.0563 0.1512 1.0000 8.250 1.3021 0.01341 0.00724 -0.0563 0.1479 1.0000 8.500 1.3298 0.01361 0.00746 -0.0564 0.1454 1.0000 8.750 1.3569 0.01386 0.00771 -0.0564 0.1423 1.0000 9.000 1.3834 0.01418 0.00800 -0.0564 0.1387 1.0000 9.250 1.4095 0.01453 0.00834 -0.0563 0.1354 1.0000 9.500 1.4365 0.01475 0.00859 -0.0563 0.1333 1.0000 9.750 1.4628 0.01502 0.00887 -0.0562 0.1304 1.0000 10.000 1.4884 0.01537 0.00920 -0.0561 0.1273 1.0000 10.250 1.5128 0.01580 0.00962 -0.0558 0.1237 1.0000 10.500 1.5389 0.01604 0.00990 -0.0556 0.1219 1.0000 10.750 1.5641 0.01635 0.01023 -0.0554 0.1194 1.0000 11.000 1.5883 0.01672 0.01060 -0.0551 0.1167 1.0000 11.250 1.6109 0.01722 0.01108 -0.0545 0.1134 1.0000 11.500 1.6348 0.01756 0.01146 -0.0541 0.1115 1.0000 11.750 1.6585 0.01790 0.01183 -0.0537 0.1094 1.0000 12.000 1.6808 0.01832 0.01226 -0.0531 0.1071 1.0000 12.250 1.7015 0.01883 0.01277 -0.0522 0.1045 1.0000 12.500 1.7206 0.01941 0.01337 -0.0512 0.1019 1.0000 12.750 1.7420 0.01979 0.01380 -0.0504 0.1004 1.0000 13.000 1.7615 0.02026 0.01431 -0.0494 0.0986 1.0000 13.250 1.7789 0.02083 0.01490 -0.0481 0.0966 1.0000 13.500 1.7931 0.02153 0.01562 -0.0464 0.0944 1.0000 13.750 1.8004 0.02240 0.01652 -0.0435 0.0924 1.0000 14.000 1.8130 0.02307 0.01726 -0.0415 0.0913 1.0000 14.250 1.8248 0.02386 0.01811 -0.0397 0.0899 1.0000 14.500 1.8356 0.02482 0.01911 -0.0380 0.0883 1.0000 14.750 1.8447 0.02596 0.02029 -0.0363 0.0867 1.0000 15.000 1.8513 0.02739 0.02177 -0.0347 0.0850 1.0000 15.250 1.8576 0.02896 0.02340 -0.0333 0.0834 1.0000 15.500 1.8690 0.03019 0.02470 -0.0325 0.0824 1.0000 15.750 1.8784 0.03164 0.02623 -0.0317 0.0812 1.0000 16.000 1.8857 0.03335 0.02800 -0.0309 0.0799 1.0000 16.250 1.8909 0.03532 0.03003 -0.0303 0.0786 1.0000 16.500 1.8928 0.03771 0.03246 -0.0297 0.0771 1.0000 16.750 1.8890 0.04076 0.03558 -0.0293 0.0754 1.0000 17.000 1.8964 0.04269 0.03761 -0.0291 0.0745 1.0000 17.250 1.9004 0.04503 0.04003 -0.0290 0.0734 1.0000 17.500 1.9008 0.04779 0.04287 -0.0290 0.0722 1.0000 17.750 1.8980 0.05097 0.04613 -0.0291 0.0711 1.0000 18.000 1.8914 0.05467 0.04990 -0.0294 0.0700 1.0000 18.250 1.8808 0.05898 0.05430 -0.0300 0.0689 1.0000 18.500 1.8666 0.06386 0.05927 -0.0308 0.0678 1.0000 18.750 1.8632 0.06745 0.06297 -0.0315 0.0672 1.0000 19.000 1.8569 0.07148 0.06711 -0.0324 0.0663 1.0000 19.250 1.8472 0.07601 0.07174 -0.0335 0.0654 1.0000