XFOIL Version 6.96 Calculated polar for: ARA-D 20% 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 ------ -------- --------- --------- -------- -------- -------- -18.750 -1.2044 0.09104 0.08718 -0.0160 1.0000 0.0174 -18.500 -1.2271 0.08362 0.07963 -0.0199 1.0000 0.0175 -18.250 -1.2493 0.07641 0.07229 -0.0236 1.0000 0.0175 -18.000 -1.2693 0.06974 0.06548 -0.0269 1.0000 0.0175 -17.750 -1.2858 0.06370 0.05931 -0.0299 1.0000 0.0176 -17.500 -1.2990 0.05823 0.05372 -0.0325 1.0000 0.0176 -17.250 -1.3082 0.05341 0.04878 -0.0347 1.0000 0.0177 -17.000 -1.3145 0.04910 0.04436 -0.0365 1.0000 0.0178 -16.750 -1.3172 0.04540 0.04056 -0.0379 1.0000 0.0179 -16.500 -1.3173 0.04213 0.03719 -0.0389 1.0000 0.0180 -16.250 -1.3153 0.03926 0.03423 -0.0396 1.0000 0.0180 -16.000 -1.3169 0.03619 0.03106 -0.0400 1.0000 0.0182 -15.750 -1.3201 0.03320 0.02797 -0.0399 1.0000 0.0184 -15.500 -1.3195 0.03085 0.02555 -0.0391 1.0000 0.0186 -15.250 -1.3162 0.02897 0.02360 -0.0379 1.0000 0.0188 -15.000 -1.3125 0.02741 0.02198 -0.0361 1.0000 0.0190 -14.750 -1.3102 0.02613 0.02064 -0.0332 1.0000 0.0192 -14.500 -1.2982 0.02519 0.01965 -0.0314 1.0000 0.0194 -14.250 -1.2823 0.02436 0.01878 -0.0300 1.0000 0.0197 -14.000 -1.2642 0.02360 0.01799 -0.0289 1.0000 0.0200 -13.750 -1.2445 0.02290 0.01724 -0.0278 1.0000 0.0204 -13.500 -1.2233 0.02225 0.01656 -0.0270 1.0000 0.0207 -13.250 -1.2006 0.02168 0.01595 -0.0263 1.0000 0.0210 -13.000 -1.1799 0.02084 0.01508 -0.0254 1.0000 0.0215 -12.750 -1.1569 0.02016 0.01439 -0.0248 1.0000 0.0220 -12.500 -1.1323 0.01960 0.01383 -0.0244 1.0000 0.0226 -12.250 -1.1067 0.01910 0.01332 -0.0240 1.0000 0.0232 -12.000 -1.0804 0.01864 0.01284 -0.0237 1.0000 0.0238 -11.750 -1.0541 0.01815 0.01232 -0.0235 1.0000 0.0245 -11.500 -1.0276 0.01758 0.01177 -0.0234 0.9934 0.0254 -11.250 -1.0017 0.01740 0.01143 -0.0226 0.8905 0.0263 -11.000 -0.9789 0.01738 0.01103 -0.0213 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0.00568 -0.0242 0.4664 0.0702 -6.000 -0.3891 0.01286 0.00550 -0.0245 0.4624 0.0766 -5.750 -0.3583 0.01267 0.00533 -0.0249 0.4578 0.0845 -5.500 -0.3275 0.01249 0.00517 -0.0253 0.4531 0.0940 -5.250 -0.2966 0.01232 0.00503 -0.0257 0.4479 0.1046 -5.000 -0.2656 0.01211 0.00488 -0.0262 0.4451 0.1164 -4.750 -0.2346 0.01192 0.00474 -0.0266 0.4415 0.1299 -4.250 -0.1724 0.01156 0.00449 -0.0276 0.4329 0.1635 -4.000 -0.1414 0.01142 0.00440 -0.0281 0.4275 0.1842 -3.750 -0.1101 0.01121 0.00429 -0.0286 0.4250 0.2067 -3.500 -0.0788 0.01101 0.00419 -0.0292 0.4215 0.2327 -3.250 -0.0476 0.01084 0.00410 -0.0297 0.4173 0.2595 -3.000 -0.0163 0.01068 0.00402 -0.0303 0.4129 0.2896 -2.750 0.0149 0.01057 0.00398 -0.0308 0.4075 0.3192 -2.500 0.0463 0.01039 0.00392 -0.0314 0.4048 0.3511 -2.250 0.0778 0.01025 0.00387 -0.0320 0.4011 0.3818 -2.000 0.1091 0.01011 0.00383 -0.0325 0.3969 0.4168 -1.750 0.1405 0.01000 0.00381 -0.0331 0.3923 0.4528 -1.500 0.1718 0.00994 0.00381 -0.0337 0.3874 0.4825 -1.250 0.2033 0.00985 0.00379 -0.0342 0.3841 0.5097 -1.000 0.2347 0.00977 0.00379 -0.0348 0.3799 0.5368 -0.750 0.2661 0.00974 0.00380 -0.0353 0.3754 0.5626 -0.500 0.2973 0.00975 0.00383 -0.0358 0.3696 0.5866 -0.250 0.3287 0.00970 0.00385 -0.0363 0.3663 0.6109 0.000 0.3601 0.00967 0.00388 -0.0369 0.3619 0.6346 0.250 0.3913 0.00968 0.00391 -0.0374 0.3572 0.6553 0.500 0.4224 0.00974 0.00397 -0.0379 0.3513 0.6747 0.750 0.4537 0.00973 0.00401 -0.0384 0.3478 0.6939 1.000 0.4848 0.00976 0.00406 -0.0389 0.3431 0.7126 1.250 0.5157 0.00981 0.00413 -0.0393 0.3380 0.7300 1.500 0.5466 0.00988 0.00421 -0.0398 0.3330 0.7464 1.750 0.5777 0.00991 0.00427 -0.0403 0.3289 0.7623 2.000 0.6084 0.00997 0.00434 -0.0407 0.3239 0.7782 2.250 0.6390 0.01007 0.00444 -0.0412 0.3185 0.7926 2.500 0.6698 0.01014 0.00452 -0.0416 0.3146 0.8068 2.750 0.7002 0.01019 0.00461 -0.0420 0.3102 0.8212 3.000 0.7305 0.01029 0.00471 -0.0424 0.3052 0.8345 3.250 0.7605 0.01043 0.00483 -0.0427 0.2998 0.8484 3.500 0.7906 0.01048 0.00493 -0.0430 0.2966 0.8615 3.750 0.8207 0.01058 0.00503 -0.0434 0.2923 0.8745 4.000 0.8498 0.01070 0.00515 -0.0436 0.2874 0.8878 4.250 0.8788 0.01083 0.00528 -0.0437 0.2828 0.9006 4.500 0.9080 0.01090 0.00538 -0.0439 0.2795 0.9139 4.750 0.9359 0.01099 0.00549 -0.0437 0.2756 0.9280 5.000 0.9626 0.01111 0.00560 -0.0434 0.2711 0.9430 5.250 0.9886 0.01119 0.00568 -0.0429 0.2670 0.9609 5.500 1.0173 0.01117 0.00568 -0.0429 0.2638 0.9860 5.750 1.0490 0.01128 0.00577 -0.0439 0.2600 1.0000 6.000 1.0797 0.01151 0.00595 -0.0446 0.2557 1.0000 6.250 1.1103 0.01173 0.00615 -0.0453 0.2518 1.0000 6.500 1.1411 0.01188 0.00630 -0.0461 0.2488 1.0000 6.750 1.1715 0.01208 0.00647 -0.0467 0.2453 1.0000 7.000 1.2014 0.01232 0.00668 -0.0473 0.2415 1.0000 7.250 1.2309 0.01260 0.00692 -0.0479 0.2374 1.0000 7.500 1.2610 0.01276 0.00709 -0.0485 0.2349 1.0000 7.750 1.2907 0.01296 0.00729 -0.0491 0.2318 1.0000 8.000 1.3199 0.01321 0.00752 -0.0496 0.2285 1.0000 8.250 1.3484 0.01354 0.00781 -0.0500 0.2244 1.0000 8.500 1.3776 0.01374 0.00802 -0.0505 0.2220 1.0000 8.750 1.4067 0.01395 0.00824 -0.0510 0.2194 1.0000 9.000 1.4352 0.01420 0.00848 -0.0514 0.2165 1.0000 9.250 1.4630 0.01451 0.00878 -0.0517 0.2132 1.0000 9.500 1.4900 0.01489 0.00913 -0.0520 0.2095 1.0000 9.750 1.5185 0.01509 0.00936 -0.0524 0.2077 1.0000 10.000 1.5463 0.01534 0.00962 -0.0527 0.2052 1.0000 10.250 1.5733 0.01564 0.00992 -0.0529 0.2023 1.0000 10.500 1.5993 0.01603 0.01029 -0.0530 0.1992 1.0000 10.750 1.6245 0.01644 0.01070 -0.0530 0.1961 1.0000 11.000 1.6515 0.01668 0.01098 -0.0532 0.1943 1.0000 11.250 1.6775 0.01699 0.01130 -0.0533 0.1919 1.0000 11.500 1.7023 0.01736 0.01168 -0.0532 0.1893 1.0000 11.750 1.7256 0.01782 0.01213 -0.0530 0.1865 1.0000 12.000 1.7473 0.01835 0.01266 -0.0525 0.1836 1.0000 12.250 1.7718 0.01866 0.01302 -0.0524 0.1819 1.0000 12.500 1.7947 0.01905 0.01344 -0.0520 0.1798 1.0000 12.750 1.8157 0.01953 0.01393 -0.0514 0.1775 1.0000 13.000 1.8341 0.02012 0.01453 -0.0505 0.1751 1.0000 13.250 1.8478 0.02091 0.01533 -0.0489 0.1722 1.0000 13.500 1.8643 0.02148 0.01595 -0.0477 0.1706 1.0000 13.750 1.8743 0.02219 0.01673 -0.0454 0.1691 1.0000 14.000 1.8829 0.02312 0.01771 -0.0432 0.1673 1.0000 14.250 1.8904 0.02428 0.01892 -0.0414 0.1654 1.0000 14.500 1.8955 0.02580 0.02048 -0.0398 0.1634 1.0000 14.750 1.8958 0.02792 0.02264 -0.0385 0.1610 1.0000 15.000 1.9017 0.02984 0.02464 -0.0380 0.1594 1.0000 15.250 1.9099 0.03172 0.02660 -0.0379 0.1579 1.0000 15.500 1.9138 0.03416 0.02911 -0.0380 0.1562 1.0000 15.750 1.9132 0.03725 0.03228 -0.0384 0.1544 1.0000 16.000 1.9064 0.04115 0.03626 -0.0390 0.1525 1.0000 16.250 1.8903 0.04613 0.04132 -0.0397 0.1504 1.0000 16.500 1.8756 0.05080 0.04608 -0.0403 0.1487 1.0000 16.750 1.8690 0.05449 0.04987 -0.0407 0.1474 1.0000 17.000 1.8573 0.05869 0.05417 -0.0411 0.1458 1.0000 17.250 1.8406 0.06342 0.05898 -0.0415 0.1441 1.0000 17.500 1.8213 0.06859 0.06422 -0.0422 0.1423 1.0000 17.750 1.7992 0.07420 0.06989 -0.0431 0.1404 1.0000 18.000 1.7852 0.07891 0.07466 -0.0439 0.1384 1.0000 18.250 1.7786 0.08287 0.07871 -0.0448 0.1371 1.0000 18.500 1.7743 0.08648 0.08238 -0.0456 0.1355 1.0000 18.750 1.7625 0.09111 0.08708 -0.0467 0.1336 1.0000 19.000 1.7505 0.09580 0.09181 -0.0478 0.1317 1.0000