XFOIL Version 6.96 Calculated polar for: AH 93-K-131/15 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4104 0.08662 0.08416 -0.0303 0.7908 0.0221 -8.500 -0.4141 0.08121 0.07877 -0.0356 0.7892 0.0226 -8.250 -0.4213 0.07545 0.07297 -0.0411 0.7876 0.0229 -8.000 -0.4294 0.07002 0.06746 -0.0441 0.7863 0.0236 -7.750 -0.4281 0.06296 0.06014 -0.0476 0.7851 0.0247 -7.500 -0.4273 0.05810 0.05506 -0.0475 0.7842 0.0248 -7.250 -0.4235 0.05343 0.05015 -0.0474 0.7818 0.0249 -6.750 -0.4548 0.03224 0.02766 -0.0400 0.7770 0.0192 -6.500 -0.4430 0.02865 0.02361 -0.0377 0.7754 0.0192 -6.250 -0.4287 0.02533 0.01987 -0.0357 0.7741 0.0195 -6.000 -0.4077 0.02380 0.01815 -0.0347 0.7729 0.0201 -5.750 -0.3848 0.02277 0.01697 -0.0339 0.7718 0.0208 -5.500 -0.3606 0.02214 0.01623 -0.0334 0.7709 0.0219 -5.250 -0.3364 0.02117 0.01506 -0.0326 0.7700 0.0232 -5.000 -0.3090 0.02017 0.01387 -0.0327 0.7670 0.0242 -4.750 -0.2819 0.01951 0.01304 -0.0326 0.7646 0.0250 -4.500 -0.2571 0.01758 0.01099 -0.0322 0.7628 0.0267 -4.250 -0.2307 0.01709 0.01047 -0.0321 0.7612 0.0282 -4.000 -0.2042 0.01670 0.01002 -0.0318 0.7598 0.0303 -3.750 -0.1776 0.01624 0.00948 -0.0315 0.7586 0.0319 -3.500 -0.1524 0.01540 0.00855 -0.0309 0.7576 0.0334 -3.250 -0.1280 0.01467 0.00779 -0.0302 0.7565 0.0361 -3.000 -0.1019 0.01437 0.00746 -0.0298 0.7554 0.0389 -2.750 -0.0736 0.01420 0.00729 -0.0303 0.7517 0.0414 -2.500 -0.0479 0.01375 0.00681 -0.0300 0.7492 0.0442 -2.250 -0.0220 0.01336 0.00643 -0.0297 0.7473 0.0494 -2.000 0.0047 0.01309 0.00612 -0.0294 0.7458 0.0540 -1.750 0.0303 0.01266 0.00569 -0.0289 0.7444 0.0634 -1.500 0.0563 0.01228 0.00536 -0.0285 0.7432 0.0847 -1.250 0.0782 0.01149 0.00508 -0.0275 0.7420 0.2238 -1.000 0.0943 0.01046 0.00503 -0.0259 0.7389 0.4969 -0.750 0.1668 0.00956 0.00560 -0.0347 0.7378 0.9312 -0.500 0.1998 0.00985 0.00584 -0.0355 0.7351 0.9515 -0.250 0.2441 0.01008 0.00599 -0.0387 0.7333 0.9650 0.000 0.3012 0.01026 0.00609 -0.0446 0.7319 0.9782 0.250 0.3923 0.01016 0.00590 -0.0578 0.7312 0.9973 0.500 0.4298 0.00994 0.00562 -0.0600 0.7296 1.0000 0.750 0.4547 0.00980 0.00541 -0.0596 0.7279 1.0000 1.000 0.4822 0.00979 0.00540 -0.0599 0.7246 1.0000 1.250 0.5093 0.00975 0.00536 -0.0601 0.7210 1.0000 1.500 0.5354 0.00964 0.00522 -0.0600 0.7183 1.0000 1.750 0.5611 0.00949 0.00504 -0.0596 0.7159 1.0000 2.000 0.5863 0.00934 0.00483 -0.0592 0.7136 1.0000 2.250 0.6141 0.00933 0.00486 -0.0595 0.7090 1.0000 2.500 0.6408 0.00924 0.00477 -0.0595 0.7050 1.0000 2.750 0.6667 0.00910 0.00460 -0.0592 0.7017 1.0000 3.000 0.6927 0.00898 0.00445 -0.0589 0.6985 1.0000 3.250 0.7207 0.00898 0.00450 -0.0593 0.6930 1.0000 3.500 0.7472 0.00888 0.00441 -0.0592 0.6887 1.0000 3.750 0.7733 0.00877 0.00426 -0.0589 0.6850 1.0000 4.000 0.8012 0.00878 0.00434 -0.0593 0.6784 1.0000 4.250 0.8279 0.00869 0.00426 -0.0592 0.6731 1.0000 4.500 0.8550 0.00867 0.00427 -0.0593 0.6661 1.0000 4.750 0.8818 0.00861 0.00422 -0.0592 0.6587 1.0000 5.000 0.9091 0.00862 0.00427 -0.0594 0.6500 1.0000 5.250 0.9359 0.00860 0.00426 -0.0594 0.6387 1.0000 5.500 0.9628 0.00863 0.00428 -0.0594 0.6248 1.0000 5.750 0.9897 0.00870 0.00435 -0.0595 0.6115 1.0000 6.000 1.0164 0.00882 0.00447 -0.0597 0.5946 1.0000 6.250 1.0427 0.00901 0.00463 -0.0598 0.5735 1.0000 6.500 1.0686 0.00928 0.00484 -0.0599 0.5496 1.0000 6.750 1.0935 0.00966 0.00514 -0.0600 0.5221 1.0000 7.000 1.1172 0.01016 0.00554 -0.0599 0.4895 1.0000 7.250 1.1384 0.01085 0.00608 -0.0596 0.4519 1.0000 7.500 1.1550 0.01182 0.00683 -0.0588 0.4024 1.0000 7.750 1.1659 0.01302 0.00777 -0.0572 0.3518 1.0000 8.000 1.1716 0.01430 0.00884 -0.0549 0.3080 1.0000 8.250 1.1699 0.01555 0.00991 -0.0511 0.2729 1.0000 8.500 1.1557 0.01657 0.01080 -0.0445 0.2485 1.0000 8.750 1.1463 0.01764 0.01172 -0.0390 0.2196 1.0000 9.000 1.1404 0.01878 0.01270 -0.0343 0.1887 1.0000 9.250 1.1370 0.01995 0.01370 -0.0301 0.1586 1.0000 9.500 1.1357 0.02112 0.01471 -0.0264 0.1309 1.0000 9.750 1.1360 0.02230 0.01575 -0.0231 0.1076 1.0000 10.000 1.1399 0.02336 0.01672 -0.0204 0.0892 1.0000 10.250 1.1444 0.02444 0.01773 -0.0178 0.0744 1.0000 10.500 1.1499 0.02553 0.01876 -0.0155 0.0617 1.0000 10.750 1.1555 0.02665 0.01984 -0.0132 0.0510 1.0000 11.000 1.1613 0.02782 0.02099 -0.0111 0.0417 1.0000 11.250 1.1666 0.02908 0.02223 -0.0090 0.0338 1.0000 11.500 1.1702 0.03052 0.02364 -0.0069 0.0273 1.0000 11.750 1.1771 0.03181 0.02495 -0.0052 0.0231 1.0000 12.000 1.1815 0.03338 0.02656 -0.0034 0.0199 1.0000 12.250 1.1887 0.03478 0.02801 -0.0020 0.0178 1.0000 12.500 1.1900 0.03672 0.02999 -0.0002 0.0160 1.0000 12.750 1.1943 0.03850 0.03186 0.0012 0.0150 1.0000 13.000 1.2007 0.04014 0.03359 0.0024 0.0141 1.0000 13.250 1.2061 0.04191 0.03543 0.0035 0.0133 1.0000 13.500 1.2104 0.04383 0.03742 0.0046 0.0127 1.0000 13.750 1.2112 0.04614 0.03979 0.0057 0.0121 1.0000 14.000 1.2050 0.04915 0.04289 0.0072 0.0116 1.0000 14.250 1.2088 0.05128 0.04512 0.0080 0.0112 1.0000 14.500 1.2144 0.05330 0.04723 0.0086 0.0109 1.0000 14.750 1.2186 0.05550 0.04953 0.0092 0.0105 1.0000 15.000 1.2218 0.05783 0.05195 0.0097 0.0101 1.0000 15.250 1.2241 0.06029 0.05451 0.0102 0.0098 1.0000 15.500 1.2260 0.06286 0.05717 0.0105 0.0095 1.0000 15.750 1.2272 0.06556 0.05996 0.0108 0.0093 1.0000 16.000 1.2278 0.06836 0.06285 0.0110 0.0091 1.0000 16.250 1.2273 0.07130 0.06587 0.0112 0.0089 1.0000 16.500 1.2256 0.07442 0.06908 0.0114 0.0087 1.0000 16.750 1.2225 0.07768 0.07246 0.0117 0.0085 1.0000 17.000 1.2172 0.08117 0.07609 0.0122 0.0084 1.0000 17.250 1.2122 0.08486 0.07993 0.0122 0.0083 1.0000 17.500 1.2089 0.08866 0.08387 0.0116 0.0082 1.0000 17.750 1.2043 0.09271 0.08808 0.0107 0.0082 1.0000 18.000 1.1984 0.09704 0.09257 0.0096 0.0081 1.0000 18.250 1.1911 0.10168 0.09737 0.0083 0.0080 1.0000 18.500 1.1824 0.10668 0.10253 0.0067 0.0080 1.0000 18.750 1.1725 0.11202 0.10803 0.0047 0.0080 1.0000 19.000 1.1614 0.11776 0.11393 0.0024 0.0079 1.0000 19.250 1.1489 0.12389 0.12023 -0.0003 0.0079 1.0000