XFOIL Version 6.96 Calculated polar for: AH 93-W-215 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.750 -0.7834 0.10879 0.10367 -0.0600 1.0000 0.0472 -18.500 -0.8188 0.09908 0.09370 -0.0653 1.0000 0.0478 -18.250 -0.8450 0.09126 0.08563 -0.0696 1.0000 0.0484 -18.000 -0.8497 0.08723 0.08156 -0.0715 1.0000 0.0489 -17.750 -0.8530 0.08347 0.07777 -0.0733 1.0000 0.0495 -17.500 -0.8577 0.07955 0.07378 -0.0751 1.0000 0.0500 -17.250 -0.8628 0.07563 0.06979 -0.0769 1.0000 0.0507 -17.000 -0.8679 0.07182 0.06589 -0.0785 1.0000 0.0514 -16.750 -0.8729 0.06811 0.06207 -0.0800 1.0000 0.0522 -16.500 -0.8772 0.06460 0.05844 -0.0813 1.0000 0.0530 -16.250 -0.8805 0.06131 0.05500 -0.0824 1.0000 0.0538 -16.000 -0.8809 0.05854 0.05218 -0.0832 1.0000 0.0546 -15.750 -0.8795 0.05608 0.04971 -0.0837 1.0000 0.0553 -15.500 -0.8779 0.05370 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-0.0640 0.5698 0.6055 -0.250 0.2834 0.01467 0.00657 -0.0631 0.5671 0.6172 0.000 0.3052 0.01472 0.00669 -0.0618 0.5637 0.6296 0.250 0.3279 0.01476 0.00676 -0.0608 0.5604 0.6422 0.500 0.3520 0.01478 0.00682 -0.0599 0.5573 0.6517 0.750 0.3768 0.01481 0.00684 -0.0593 0.5545 0.6612 1.000 0.4027 0.01482 0.00683 -0.0588 0.5520 0.6697 1.250 0.4286 0.01487 0.00688 -0.0584 0.5494 0.6780 1.750 0.4713 0.01500 0.00713 -0.0558 0.5423 0.6944 2.000 0.4943 0.01504 0.00719 -0.0548 0.5389 0.7033 2.250 0.5184 0.01507 0.00722 -0.0540 0.5359 0.7116 2.500 0.5441 0.01510 0.00724 -0.0535 0.5332 0.7204 2.750 0.5674 0.01517 0.00732 -0.0526 0.5302 0.7297 3.000 0.5863 0.01527 0.00753 -0.0509 0.5262 0.7381 3.250 0.6066 0.01534 0.00764 -0.0494 0.5224 0.7483 3.500 0.6289 0.01539 0.00773 -0.0483 0.5189 0.7568 3.750 0.6526 0.01543 0.00776 -0.0474 0.5159 0.7667 4.000 0.6771 0.01549 0.00782 -0.0467 0.5129 0.7760 4.250 0.6923 0.01562 0.00806 -0.0443 0.5086 0.7866 4.500 0.7100 0.01572 0.00822 -0.0424 0.5044 0.7964 4.750 0.7296 0.01578 0.00831 -0.0408 0.5006 0.8070 5.000 0.7526 0.01582 0.00834 -0.0398 0.4973 0.8171 5.250 0.7707 0.01592 0.00849 -0.0379 0.4936 0.8285 5.500 0.7823 0.01605 0.00871 -0.0348 0.4890 0.8396 5.750 0.7958 0.01613 0.00884 -0.0321 0.4846 0.8523 6.000 0.8166 0.01619 0.00892 -0.0307 0.4808 0.8636 6.250 0.8387 0.01628 0.00901 -0.0297 0.4771 0.8753 6.500 0.8514 0.01652 0.00936 -0.0271 0.4719 0.8896 6.750 0.8746 0.01671 0.00961 -0.0266 0.4670 0.9028 7.000 0.9058 0.01683 0.00974 -0.0276 0.4625 0.9151 7.250 0.9359 0.01708 0.01005 -0.0286 0.4572 0.9287 7.500 0.9690 0.01740 0.01046 -0.0304 0.4510 0.9424 7.750 1.0087 0.01762 0.01068 -0.0333 0.4456 0.9547 8.250 1.0842 0.01843 0.01160 -0.0390 0.4327 1.0000 8.500 1.0956 0.01867 0.01178 -0.0365 0.4276 1.0000 8.750 1.1038 0.01908 0.01222 -0.0337 0.4221 1.0000 9.000 1.1114 0.01956 0.01273 -0.0310 0.4157 1.0000 9.250 1.1245 0.01996 0.01308 -0.0291 0.4102 1.0000 9.500 1.1321 0.02061 0.01376 -0.0267 0.4038 1.0000 9.750 1.1407 0.02129 0.01446 -0.0246 0.3971 1.0000 10.000 1.1543 0.02184 0.01496 -0.0231 0.3915 1.0000 10.250 1.1597 0.02284 0.01605 -0.0211 0.3846 1.0000 10.500 1.1694 0.02371 0.01691 -0.0196 0.3781 1.0000 10.750 1.1780 0.02469 0.01790 -0.0182 0.3712 1.0000 11.000 1.1847 0.02589 0.01914 -0.0168 0.3640 1.0000 11.250 1.1954 0.02684 0.02004 -0.0156 0.3572 1.0000 11.500 1.1996 0.02836 0.02164 -0.0144 0.3498 1.0000 11.750 1.2079 0.02956 0.02281 -0.0134 0.3425 1.0000 12.000 1.2137 0.03104 0.02434 -0.0124 0.3354 1.0000 12.250 1.2198 0.03253 0.02585 -0.0115 0.3283 1.0000 12.500 1.2267 0.03395 0.02726 -0.0106 0.3212 1.0000 12.750 1.2301 0.03572 0.02908 -0.0097 0.3134 1.0000 13.000 1.2364 0.03721 0.03053 -0.0089 0.3060 1.0000 13.250 1.2387 0.03917 0.03257 -0.0081 0.2982 1.0000 13.500 1.2443 0.04078 0.03414 -0.0074 0.2909 1.0000 13.750 1.2465 0.04285 0.03627 -0.0068 0.2834 1.0000 14.000 1.2505 0.04471 0.03811 -0.0062 0.2757 1.0000 14.250 1.2532 0.04681 0.04027 -0.0057 0.2683 1.0000 14.500 1.2559 0.04889 0.04235 -0.0052 0.2606 1.0000 14.750 1.2581 0.05110 0.04458 -0.0049 0.2530 1.0000 15.000 1.2592 0.05344 0.04692 -0.0045 0.2448 1.0000 15.250 1.2611 0.05577 0.04927 -0.0043 0.2374 1.0000 15.500 1.2624 0.05816 0.05168 -0.0041 0.2298 1.0000 15.750 1.2630 0.06068 0.05422 -0.0039 0.2223 1.0000 16.000 1.2646 0.06316 0.05673 -0.0039 0.2153 1.0000 16.250 1.2653 0.06573 0.05930 -0.0038 0.2085 1.0000 16.500 1.2651 0.06847 0.06209 -0.0039 0.2010 1.0000 16.750 1.2652 0.07116 0.06476 -0.0039 0.1946 1.0000 17.000 1.2652 0.07398 0.06764 -0.0041 0.1875 1.0000 17.500 1.2640 0.07977 0.07349 -0.0046 0.1746 1.0000 17.750 1.2617 0.08287 0.07659 -0.0050 0.1684 1.0000 18.000 1.2609 0.08589 0.07966 -0.0054 0.1621 1.0000 18.250 1.2578 0.08921 0.08299 -0.0059 0.1558 1.0000 18.500 1.2563 0.09237 0.08619 -0.0065 0.1499 1.0000 18.750 1.2536 0.09569 0.08955 -0.0071 0.1441 1.0000 19.000 1.2506 0.09908 0.09294 -0.0078 0.1384 1.0000 19.250 1.2475 0.10253 0.09646 -0.0086 0.1325 1.0000