XFOIL Version 6.96 Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN 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 ------ -------- --------- --------- -------- -------- -------- -9.500 -0.3961 0.08657 0.08404 -0.0490 -0.0009 4.4416 -9.250 -0.4131 0.08159 0.07910 -0.0515 -0.0009 4.4416 -9.000 -0.4300 0.07731 0.07481 -0.0533 -0.0009 4.4417 -8.750 -0.4485 0.07365 0.07114 -0.0543 -0.0009 4.4418 -8.500 -0.4660 0.07059 0.06808 -0.0543 -0.0009 4.4419 -8.250 -0.4895 0.06751 0.06496 -0.0541 -0.0009 4.4420 -8.000 -0.5172 0.06367 0.06097 -0.0544 -0.0009 4.4417 -7.750 -0.5069 0.06165 0.05906 -0.0531 -0.0009 4.4396 -7.500 -0.5177 0.05860 0.05592 -0.0526 -0.0009 4.4373 -7.250 -0.5211 0.05516 0.05238 -0.0526 -0.0008 4.4339 -7.000 -0.5161 0.05179 0.04884 -0.0534 -0.0004 4.4270 -6.750 -0.5055 0.04893 0.04584 -0.0542 -0.0002 4.4182 -6.500 -0.4988 0.04663 0.04339 -0.0540 0.0000 4.4083 -5.000 -0.4051 0.02725 0.02156 -0.0456 -0.0014 4.4572 -4.750 -0.3787 0.02661 0.02058 -0.0450 -0.0016 4.4574 -4.500 -0.3746 0.02475 0.01867 -0.0424 -0.0015 4.4573 -4.250 -0.3515 0.02390 0.01761 -0.0416 -0.0012 4.4572 -4.000 -0.3252 0.02386 0.01744 -0.0413 -0.0010 4.4571 -3.750 -0.3186 0.02289 0.01648 -0.0391 -0.0005 4.4571 -3.500 -0.2990 0.02234 0.01592 -0.0383 -0.0001 4.4570 -3.250 -0.2739 0.02250 0.01607 -0.0383 0.0000 4.4571 -3.000 -0.2696 0.02169 0.01527 -0.0360 -0.0001 4.4571 -2.750 -0.2492 0.02149 0.01505 -0.0355 -0.0004 4.4572 -2.000 -0.1862 0.02083 0.01425 -0.0337 0.0049 4.4557 -1.750 -0.1072 0.02167 0.01763 -0.0358 0.0113 2.2548 -1.500 -0.0034 0.02552 0.02126 -0.0393 0.0116 2.0943 -1.250 0.0676 0.02715 0.02274 -0.0416 0.0124 2.0104 -1.000 0.0929 0.02713 0.02261 -0.0420 0.0147 2.0009 -0.750 0.0978 0.02670 0.02213 -0.0404 0.0221 2.0009 -0.500 0.1165 0.02642 0.02175 -0.0404 0.0255 2.0009 -0.250 0.1230 0.02608 0.02137 -0.0389 0.0329 2.0009 0.000 0.1393 0.02585 0.02106 -0.0385 0.0369 2.0009 0.250 0.1570 0.02565 0.02080 -0.0381 0.0411 2.0009 0.500 0.1646 0.02530 0.02040 -0.0366 0.0503 2.0009 0.750 0.1818 0.02510 0.02015 -0.0361 0.0559 2.0009 1.000 0.1919 0.02478 0.01979 -0.0348 0.0671 2.0009 1.250 0.2114 0.02455 0.01949 -0.0345 0.0737 2.0009 1.500 0.2209 0.02423 0.01915 -0.0330 0.0885 2.0009 1.750 0.2453 0.02402 0.01889 -0.0331 0.0925 2.0009 2.000 0.2481 0.02378 0.01865 -0.0309 0.1137 2.0009 2.250 0.2719 0.02354 0.01837 -0.0309 0.1183 2.0009 2.500 0.2739 0.02340 0.01823 -0.0286 0.1413 2.0009 2.750 0.2968 0.02312 0.01792 -0.0284 0.1470 2.0009 3.000 0.3219 0.02283 0.01760 -0.0284 0.1506 2.0009 3.250 0.3214 0.02269 0.01748 -0.0258 0.1767 2.0009 3.500 0.3465 0.02235 0.01712 -0.0257 0.1808 2.0009 3.750 0.3483 0.02219 0.01698 -0.0233 0.2069 2.0009 4.000 0.3738 0.02176 0.01655 -0.0231 0.2117 2.0009 4.250 0.3774 0.02161 0.01641 -0.0209 0.2383 2.0009 4.500 0.4020 0.02117 0.01597 -0.0206 0.2441 2.0009 4.750 0.4281 0.02070 0.01550 -0.0204 0.2479 2.0009 5.000 0.4297 0.02062 0.01545 -0.0180 0.2791 2.0009 5.250 0.4489 0.02028 0.01515 -0.0172 0.2906 2.0009 5.500 0.4573 0.02010 0.01500 -0.0154 0.3174 2.0009 5.750 0.4830 0.01956 0.01449 -0.0150 0.3226 2.0009 6.000 0.5097 0.01898 0.01394 -0.0148 0.3264 2.0009 6.250 0.5101 0.01900 0.01401 -0.0123 0.3649 2.0009 6.500 0.5142 0.01897 0.01403 -0.0101 0.3994 2.0009 6.750 0.5376 0.01839 0.01350 -0.0094 0.4091 2.0009 7.000 0.5637 0.01768 0.01285 -0.0090 0.4150 2.0009 7.250 0.5917 0.01684 0.01208 -0.0086 0.4187 2.0009 7.500 0.6210 0.01589 0.01120 -0.0083 0.4212 2.0009 7.750 0.6522 0.01486 0.01025 -0.0081 0.4237 2.0009 8.250 0.6638 0.01417 0.00970 -0.0034 0.5046 2.0009 8.500 0.7250 0.00975 0.00510 -0.0032 0.6508 2.0009 8.750 0.7399 0.00909 0.00424 -0.0012 0.8405 2.0009 9.000 0.7437 0.00900 0.00392 0.0015 1.0598 2.0009 9.250 0.7379 0.00923 0.00391 0.0048 1.2906 2.0009 9.500 0.7280 0.00963 0.00412 0.0083 1.5108 2.0009 9.750 0.7174 0.01011 0.00443 0.0116 1.7287 2.0009 10.000 0.7050 0.01069 0.00485 0.0149 1.9744 2.0009 10.250 0.6917 0.01138 0.00533 0.0180 2.2734 2.0009 10.500 0.6794 0.01210 0.00585 0.0208 2.5860 2.0009 10.750 0.6626 0.01308 0.00652 0.0237 3.0634 2.0009 11.000 0.6428 0.01425 0.00734 0.0264 3.6929 2.0009 11.250 0.6320 0.01512 0.00810 0.0286 4.0503 2.0009 11.500 0.6315 0.01556 0.00863 0.0304 4.0762 2.0009 11.750 0.6309 0.01602 0.00918 0.0320 4.0883 2.0009 12.000 0.6307 0.01647 0.00975 0.0335 4.0977 2.0009 12.250 0.6303 0.01695 0.01034 0.0350 4.1040 2.0009 12.500 0.6293 0.01747 0.01098 0.0364 4.1084 2.0009 12.750 0.6275 0.01805 0.01167 0.0378 4.1120 2.0009 13.000 0.6252 0.01867 0.01241 0.0391 4.1140 2.0009 13.250 0.6221 0.01935 0.01321 0.0403 4.1154 2.0009 13.500 0.6181 0.02010 0.01407 0.0414 4.1165 2.0009 13.750 0.6138 0.02089 0.01498 0.0424 4.1165 2.0009 14.000 0.6080 0.02180 0.01600 0.0433 4.1173 2.0009 14.250 0.6034 0.02266 0.01697 0.0441 4.1167 2.0009 14.500 0.5978 0.02362 0.01803 0.0448 4.1168 2.0009 14.750 0.5929 0.02455 0.01905 0.0454 4.1165 2.0009 15.000 0.5896 0.02540 0.01999 0.0461 4.1151 2.0009 15.250 0.5873 0.02618 0.02083 0.0467 4.1141 2.0009 15.500 0.5872 0.02679 0.02150 0.0474 4.1122 2.0009 15.750 0.5900 0.02722 0.02196 0.0482 4.1103 2.0009 16.000 0.5971 0.02736 0.02214 0.0494 4.1065 2.0009 16.250 0.6100 0.02719 0.02198 0.0508 4.1016 2.0009 16.500 0.6359 0.02658 0.02131 0.0527 4.0945 2.0009 16.750 0.6618 0.02641 0.02116 0.0544 4.0858 2.0009 17.000 0.7310 0.02680 0.02153 0.0569 4.0585 2.0009 17.250 0.7034 0.02765 0.02273 0.0573 4.0535 2.0009 17.500 0.7361 0.02926 0.02451 0.0589 4.0255 2.0009 18.000 0.7482 0.03380 0.02960 0.0609 3.9613 2.0009 18.250 0.7170 0.03466 0.03069 0.0608 3.9626 2.0009 18.500 0.6816 0.03585 0.03215 0.0599 3.9659 2.0009 18.750 0.6829 0.03864 0.03514 0.0605 3.9275 2.0009 19.000 0.6575 0.04030 0.03699 0.0594 3.9280 2.0009 19.250 0.6311 0.04235 0.03921 0.0579 3.9285 2.0009