XFOIL Version 6.96 Calculated polar for: AH 88-K-136/16 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.750 -0.6525 0.04444 0.04093 -0.0995 0.7843 0.0075 -12.500 -0.6586 0.04229 0.03871 -0.0980 0.7833 0.0077 -12.250 -0.6991 0.03742 0.03351 -0.0932 0.7814 0.0076 -12.000 -0.6968 0.03621 0.03222 -0.0908 0.7800 0.0077 -11.750 -0.6987 0.03469 0.03058 -0.0877 0.7786 0.0080 -11.500 -0.7047 0.03282 0.02850 -0.0837 0.7773 0.0081 -11.250 -0.7102 0.03097 0.02643 -0.0794 0.7762 0.0082 -11.000 -0.7119 0.02946 0.02471 -0.0752 0.7752 0.0083 -10.750 -0.7083 0.02816 0.02320 -0.0718 0.7743 0.0085 -10.500 -0.7022 0.02663 0.02140 -0.0688 0.7735 0.0088 -10.250 -0.6919 0.02532 0.01986 -0.0663 0.7729 0.0090 -10.000 -0.6798 0.02407 0.01839 -0.0640 0.7722 0.0092 -9.750 -0.6642 0.02309 0.01721 -0.0622 0.7716 0.0094 -9.500 -0.6493 0.02197 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0.01348 0.00627 -0.0451 0.7510 0.0287 -4.500 -0.2000 0.01328 0.00605 -0.0446 0.7497 0.0318 -4.250 -0.1756 0.01304 0.00581 -0.0441 0.7485 0.0355 -4.000 -0.1508 0.01284 0.00560 -0.0436 0.7476 0.0398 -3.750 -0.1261 0.01261 0.00539 -0.0432 0.7466 0.0454 -3.500 -0.1008 0.01241 0.00517 -0.0428 0.7457 0.0511 -3.250 -0.0758 0.01218 0.00496 -0.0423 0.7449 0.0591 -3.000 -0.0505 0.01197 0.00477 -0.0419 0.7442 0.0685 -2.750 -0.0252 0.01175 0.00457 -0.0416 0.7435 0.0810 -2.500 0.0001 0.01154 0.00439 -0.0412 0.7428 0.0963 -2.250 0.0239 0.01142 0.00436 -0.0406 0.7409 0.1170 -2.000 0.0469 0.01131 0.00438 -0.0399 0.7382 0.1456 -1.750 0.0703 0.01109 0.00430 -0.0393 0.7361 0.1866 -1.500 0.0921 0.01070 0.00416 -0.0383 0.7344 0.2595 -1.250 0.1076 0.00997 0.00397 -0.0361 0.7328 0.4178 -1.000 0.1159 0.00915 0.00375 -0.0322 0.7313 0.5892 -0.750 0.1673 0.00852 0.00416 -0.0368 0.7305 0.8676 -0.500 0.1839 0.00863 0.00423 -0.0340 0.7293 0.8947 -0.250 0.2086 0.00877 0.00433 -0.0331 0.7279 0.9088 0.000 0.2453 0.00917 0.00474 -0.0349 0.7241 0.9179 0.250 0.2614 0.00929 0.00485 -0.0322 0.7209 0.9282 0.500 0.3357 0.00965 0.00517 -0.0420 0.7193 0.9312 0.750 0.3782 0.00970 0.00518 -0.0452 0.7174 0.9334 1.000 0.4095 0.00961 0.00506 -0.0461 0.7154 0.9351 1.250 0.4384 0.00954 0.00497 -0.0464 0.7132 0.9372 1.500 0.4460 0.00962 0.00508 -0.0422 0.7084 0.9435 1.750 0.4787 0.00957 0.00503 -0.0435 0.7048 0.9441 2.000 0.5109 0.00947 0.00491 -0.0446 0.7018 0.9448 2.250 0.5424 0.00938 0.00480 -0.0456 0.6988 0.9455 2.500 0.5714 0.00942 0.00489 -0.0462 0.6929 0.9464 2.750 0.6012 0.00936 0.00483 -0.0468 0.6884 0.9473 3.000 0.6304 0.00929 0.00475 -0.0472 0.6836 0.9483 3.250 0.6573 0.00930 0.00480 -0.0473 0.6765 0.9495 3.500 0.6845 0.00921 0.00469 -0.0474 0.6703 0.9507 3.750 0.7093 0.00923 0.00474 -0.0470 0.6606 0.9525 4.000 0.7307 0.00921 0.00472 -0.0458 0.6513 0.9544 4.250 0.7405 0.00919 0.00468 -0.0420 0.6396 0.9581 4.500 0.7684 0.00921 0.00467 -0.0423 0.6236 0.9587 4.750 0.7949 0.00929 0.00470 -0.0423 0.6050 0.9593 5.000 0.8195 0.00943 0.00479 -0.0420 0.5829 0.9602 5.250 0.8420 0.00967 0.00494 -0.0413 0.5576 0.9613 5.500 0.8624 0.01002 0.00519 -0.0403 0.5283 0.9628 5.750 0.8768 0.01053 0.00555 -0.0381 0.4920 0.9651 6.000 0.8787 0.01121 0.00603 -0.0337 0.4477 0.9688 6.250 0.8802 0.01197 0.00659 -0.0294 0.4068 0.9723 6.500 0.8904 0.01306 0.00742 -0.0276 0.3523 0.9746 6.750 0.8923 0.01396 0.00814 -0.0242 0.3144 0.9779 7.000 0.8881 0.01497 0.00897 -0.0198 0.2754 0.9822 7.250 0.8964 0.01596 0.00977 -0.0179 0.2371 0.9846 7.500 0.9067 0.01705 0.01062 -0.0166 0.1903 0.9862 7.750 0.9155 0.01818 0.01149 -0.0151 0.1422 0.9880 8.000 0.9240 0.01931 0.01239 -0.0134 0.0999 0.9899 8.250 0.9319 0.02046 0.01333 -0.0116 0.0615 0.9918 8.500 0.9414 0.02153 0.01425 -0.0100 0.0363 0.9934 8.750 0.9568 0.02234 0.01504 -0.0091 0.0277 0.9950 9.000 0.9733 0.02317 0.01585 -0.0086 0.0218 0.9967 9.250 0.9910 0.02389 0.01660 -0.0081 0.0188 0.9979 9.500 1.0074 0.02475 0.01747 -0.0076 0.0166 0.9990 9.750 1.0252 0.02554 0.01833 -0.0073 0.0153 0.9998 10.000 1.0342 0.02627 0.01911 -0.0052 0.0145 1.0000 10.250 1.0390 0.02703 0.01990 -0.0023 0.0135 1.0000 10.500 1.0417 0.02791 0.02081 0.0008 0.0127 1.0000 10.750 1.0473 0.02866 0.02162 0.0034 0.0121 1.0000 11.000 1.0537 0.02942 0.02243 0.0058 0.0115 1.0000 11.250 1.0600 0.03028 0.02334 0.0081 0.0108 1.0000 11.500 1.0666 0.03127 0.02438 0.0102 0.0104 1.0000 11.750 1.0731 0.03240 0.02556 0.0121 0.0100 1.0000 12.000 1.0769 0.03386 0.02707 0.0140 0.0096 1.0000 12.250 1.0851 0.03506 0.02834 0.0154 0.0093 1.0000 12.500 1.0921 0.03642 0.02978 0.0168 0.0089 1.0000 12.750 1.0998 0.03778 0.03121 0.0180 0.0086 1.0000 13.000 1.1075 0.03919 0.03268 0.0191 0.0082 1.0000 13.250 1.1154 0.04063 0.03419 0.0201 0.0079 1.0000 13.500 1.1192 0.04248 0.03613 0.0213 0.0078 1.0000 13.750 1.1279 0.04392 0.03761 0.0220 0.0073 1.0000 14.000 1.1294 0.04610 0.03984 0.0230 0.0070 1.0000 14.250 1.1322 0.04822 0.04207 0.0239 0.0068 1.0000 14.500 1.1368 0.05021 0.04414 0.0245 0.0069 1.0000 14.750 1.1432 0.05208 0.04611 0.0250 0.0065 1.0000 15.000 1.1456 0.05440 0.04854 0.0256 0.0063 1.0000 15.250 1.1488 0.05671 0.05095 0.0259 0.0062 1.0000 15.500 1.1485 0.05944 0.05379 0.0263 0.0063 1.0000 15.750 1.1513 0.06191 0.05636 0.0264 0.0059 1.0000 16.000 1.1518 0.06469 0.05925 0.0265 0.0058 1.0000 16.250 1.1533 0.06745 0.06210 0.0264 0.0057 1.0000 16.500 1.1534 0.07043 0.06518 0.0261 0.0055 1.0000 16.750 1.1553 0.07329 0.06813 0.0257 0.0054 1.0000 17.000 1.1510 0.07690 0.07185 0.0253 0.0054 1.0000 17.250 1.1493 0.08032 0.07539 0.0247 0.0053 1.0000 17.500 1.1486 0.08372 0.07887 0.0238 0.0052 1.0000 17.750 1.1437 0.08771 0.08298 0.0229 0.0052 1.0000 18.000 1.1375 0.09198 0.08734 0.0216 0.0050 1.0000 18.250 1.1283 0.09673 0.09220 0.0203 0.0049 1.0000 18.500 1.1252 0.10074 0.09636 0.0190 0.0050 1.0000 18.750 1.1143 0.10596 0.10171 0.0173 0.0049 1.0000 19.000 1.1086 0.11056 0.10643 0.0155 0.0049 1.0000