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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.250 -0.2161 0.16038 0.15690 -0.0404 1.0000 0.0857 -17.000 -0.8164 0.08110 0.07606 -0.0815 1.0000 0.0671 -16.750 -0.8664 0.07214 0.06679 -0.0861 1.0000 0.0671 -16.500 -0.8437 0.07166 0.06646 -0.0853 1.0000 0.0683 -16.250 -0.8557 0.06758 0.06229 -0.0867 1.0000 0.0689 -16.000 -0.8664 0.06390 0.05851 -0.0878 1.0000 0.0696 -15.750 -0.8792 0.06018 0.05467 -0.0887 1.0000 0.0702 -15.500 -0.8917 0.05668 0.05103 -0.0893 1.0000 0.0709 -15.250 -0.9039 0.05349 0.04770 -0.0894 1.0000 0.0718 -15.000 -0.9171 0.05042 0.04446 -0.0891 1.0000 0.0726 -14.750 -0.9314 0.04758 0.04141 -0.0882 1.0000 0.0734 -14.500 -0.9466 0.04504 0.03866 -0.0868 1.0000 0.0741 -14.250 -0.9474 0.04309 0.03664 -0.0854 1.0000 0.0752 -14.000 -0.9302 0.04211 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0.4396 -4.250 -0.0964 0.01662 0.00941 -0.0791 0.6640 0.4671 -4.000 -0.0781 0.01667 0.00954 -0.0772 0.6602 0.4911 -3.750 -0.0574 0.01674 0.00964 -0.0757 0.6567 0.5126 -3.500 -0.0347 0.01682 0.00972 -0.0746 0.6536 0.5317 -3.250 -0.0104 0.01693 0.00980 -0.0737 0.6510 0.5492 -3.000 0.0152 0.01712 0.00993 -0.0732 0.6483 0.5657 -2.750 0.0339 0.01729 0.01015 -0.0713 0.6448 0.5795 -2.500 0.0544 0.01742 0.01035 -0.0698 0.6409 0.5920 -2.250 0.0756 0.01755 0.01046 -0.0684 0.6375 0.6055 -2.000 0.1006 0.01766 0.01060 -0.0677 0.6344 0.6172 -1.750 0.1265 0.01773 0.01064 -0.0671 0.6315 0.6290 -1.500 0.1543 0.01786 0.01072 -0.0669 0.6289 0.6408 -1.250 0.1763 0.01807 0.01096 -0.0657 0.6257 0.6509 -1.000 0.1936 0.01827 0.01123 -0.0637 0.6218 0.6617 -0.750 0.2155 0.01840 0.01140 -0.0624 0.6180 0.6716 -0.500 0.2399 0.01849 0.01149 -0.0616 0.6146 0.6825 -0.250 0.2671 0.01854 0.01153 -0.0613 0.6118 0.6927 0.000 0.2949 0.01867 0.01162 -0.0610 0.6094 0.7047 0.250 0.3189 0.01893 0.01192 -0.0601 0.6063 0.7148 0.500 0.3316 0.01917 0.01225 -0.0573 0.6017 0.7259 0.750 0.3531 0.01931 0.01244 -0.0560 0.5978 0.7344 1.000 0.3779 0.01939 0.01253 -0.0553 0.5946 0.7439 1.250 0.4060 0.01936 0.01245 -0.0552 0.5918 0.7528 1.500 0.4377 0.01942 0.01248 -0.0556 0.5894 0.7609 1.750 0.4529 0.01966 0.01275 -0.0534 0.5856 0.7711 2.000 0.4667 0.01994 0.01316 -0.0508 0.5809 0.7786 2.250 0.4870 0.02002 0.01324 -0.0493 0.5771 0.7890 2.500 0.5154 0.01998 0.01321 -0.0492 0.5739 0.7970 2.750 0.5459 0.01995 0.01314 -0.0495 0.5714 0.8064 3.000 0.5789 0.02000 0.01312 -0.0503 0.5690 0.8154 3.250 0.5775 0.02041 0.01372 -0.0450 0.5634 0.8262 3.500 0.5937 0.02051 0.01388 -0.0428 0.5590 0.8365 3.750 0.6189 0.02049 0.01386 -0.0421 0.5557 0.8471 4.000 0.6505 0.02036 0.01369 -0.0426 0.5530 0.8565 4.250 0.6861 0.02028 0.01354 -0.0437 0.5506 0.8667 4.500 0.6825 0.02068 0.01413 -0.0381 0.5450 0.8801 4.750 0.6951 0.02078 0.01430 -0.0353 0.5403 0.8934 5.000 0.7213 0.02064 0.01414 -0.0347 0.5369 0.9065 5.250 0.7639 0.02044 0.01390 -0.0372 0.5341 0.9155 5.500 0.8064 0.02037 0.01376 -0.0399 0.5314 0.9254 5.750 0.8135 0.02089 0.01449 -0.0369 0.5246 0.9412 6.000 0.8565 0.02090 0.01452 -0.0400 0.5201 0.9500 6.250 0.9093 0.02074 0.01430 -0.0447 0.5167 0.9555 6.500 0.9696 0.02059 0.01403 -0.0507 0.5135 0.9582 6.750 0.9936 0.02121 0.01486 -0.0512 0.5062 0.9683 7.000 1.0420 0.02120 0.01485 -0.0554 0.5013 0.9727 7.250 1.0950 0.02097 0.01454 -0.0601 0.4975 0.9770 7.500 1.1322 0.02131 0.01496 -0.0627 0.4917 0.9843 7.750 1.1688 0.02151 0.01522 -0.0651 0.4853 0.9934 8.000 1.2198 0.02128 0.01492 -0.0697 0.4805 0.9987 8.250 1.2263 0.02129 0.01493 -0.0664 0.4761 1.0000 8.500 1.1798 0.02151 0.01522 -0.0537 0.4715 1.0000 8.750 1.1823 0.02152 0.01521 -0.0493 0.4665 1.0000 9.000 1.2182 0.02127 0.01485 -0.0507 0.4619 1.0000 9.250 1.2079 0.02171 0.01534 -0.0443 0.4566 1.0000 9.500 1.2074 0.02204 0.01572 -0.0398 0.4506 1.0000 9.750 1.2365 0.02190 0.01550 -0.0400 0.4455 1.0000 10.000 1.2432 0.02232 0.01595 -0.0368 0.4399 1.0000 10.250 1.2425 0.02287 0.01656 -0.0327 0.4333 1.0000 10.500 1.2715 0.02275 0.01636 -0.0329 0.4276 1.0000 10.750 1.2693 0.02354 0.01722 -0.0290 0.4209 1.0000 11.000 1.2767 0.02409 0.01779 -0.0266 0.4142 1.0000 11.250 1.3102 0.02394 0.01752 -0.0273 0.4083 1.0000 11.500 1.2934 0.02545 0.01920 -0.0225 0.4008 1.0000 11.750 1.3118 0.02578 0.01949 -0.0216 0.3944 1.0000 12.000 1.3169 0.02677 0.02051 -0.0197 0.3873 1.0000 12.250 1.3193 0.02792 0.02171 -0.0177 0.3797 1.0000 12.500 1.3407 0.02822 0.02193 -0.0172 0.3729 1.0000 12.750 1.3299 0.03027 0.02410 -0.0147 0.3646 1.0000 13.000 1.3590 0.03012 0.02381 -0.0147 0.3577 1.0000 13.250 1.3408 0.03285 0.02671 -0.0122 0.3493 1.0000 13.500 1.3593 0.03330 0.02708 -0.0117 0.3420 1.0000 13.750 1.3499 0.03573 0.02962 -0.0100 0.3336 1.0000 14.000 1.3614 0.03670 0.03054 -0.0093 0.3260 1.0000 14.250 1.3568 0.03895 0.03286 -0.0081 0.3177 1.0000 14.500 1.3633 0.04034 0.03422 -0.0073 0.3096 1.0000 14.750 1.3613 0.04252 0.03646 -0.0064 0.3016 1.0000 15.000 1.3640 0.04433 0.03826 -0.0056 0.2934 1.0000 15.250 1.3641 0.04645 0.04041 -0.0049 0.2856 1.0000 15.500 1.3647 0.04857 0.04255 -0.0044 0.2776 1.0000 15.750 1.3665 0.05064 0.04463 -0.0038 0.2699 1.0000 16.000 1.3650 0.05309 0.04711 -0.0034 0.2620 1.0000 16.250 1.3684 0.05508 0.04909 -0.0030 0.2544 1.0000 16.500 1.3641 0.05793 0.05200 -0.0028 0.2464 1.0000 16.750 1.3681 0.05994 0.05397 -0.0025 0.2390 1.0000 17.000 1.3622 0.06310 0.05721 -0.0025 0.2310 1.0000 17.250 1.3671 0.06505 0.05910 -0.0023 0.2239 1.0000 17.500 1.3593 0.06855 0.06270 -0.0024 0.2162 1.0000 17.750 1.3642 0.07053 0.06461 -0.0023 0.2090 1.0000 18.000 1.3546 0.07440 0.06859 -0.0027 0.2014 1.0000 18.250 1.3589 0.07648 0.07058 -0.0027 0.1943 1.0000 18.500 1.3485 0.08056 0.07479 -0.0032 0.1871 1.0000 18.750 1.3536 0.08257 0.07669 -0.0033 0.1803 1.0000 19.000 1.3415 0.08700 0.08127 -0.0041 0.1732 1.0000 19.250 1.3467 0.08904 0.08318 -0.0043 0.1666 1.0000