XFOIL Version 6.96 Calculated polar for: FX 71-L-150/30 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -15.000 -0.8655 0.09791 0.09351 -0.0208 1.0000 0.0373 -14.750 -0.8630 0.09400 0.08960 -0.0221 1.0000 0.0369 -14.500 -0.8799 0.08760 0.08309 -0.0255 1.0000 0.0365 -14.250 -0.9068 0.08038 0.07570 -0.0294 1.0000 0.0361 -14.000 -0.9341 0.07376 0.06886 -0.0325 1.0000 0.0356 -13.750 -0.9621 0.06759 0.06244 -0.0348 1.0000 0.0350 -13.500 -0.9985 0.06109 0.05555 -0.0363 1.0000 0.0342 -13.250 -1.0551 0.05472 0.04852 -0.0362 1.0000 0.0333 -13.000 -1.0711 0.05216 0.04566 -0.0350 1.0000 0.0331 -12.750 -1.0636 0.04939 0.04275 -0.0344 1.0000 0.0329 -12.500 -1.0599 0.04677 0.03995 -0.0335 1.0000 0.0328 -12.250 -1.0537 0.04433 0.03734 -0.0325 1.0000 0.0327 -12.000 -1.0476 0.04206 0.03487 -0.0313 1.0000 0.0327 -11.750 -1.0353 0.03997 0.03261 -0.0304 1.0000 0.0327 -11.500 -1.0227 0.03803 0.03048 -0.0294 1.0000 0.0327 -11.250 -1.0075 0.03627 0.02855 -0.0285 1.0000 0.0328 -11.000 -0.9904 0.03466 0.02677 -0.0277 1.0000 0.0330 -10.750 -0.9592 0.03288 0.02501 -0.0282 1.0000 0.0335 -10.500 -0.9347 0.03155 0.02371 -0.0280 1.0000 0.0340 -10.250 -0.9139 0.03037 0.02254 -0.0274 1.0000 0.0345 -10.000 -0.8940 0.02923 0.02139 -0.0267 1.0000 0.0350 -9.750 -0.8757 0.02812 0.02026 -0.0259 1.0000 0.0358 -9.500 -0.8586 0.02705 0.01917 -0.0250 1.0000 0.0365 -9.250 -0.8429 0.02600 0.01807 -0.0240 1.0000 0.0374 -9.000 -0.8309 0.02480 0.01697 -0.0227 1.0000 0.0384 -8.750 -0.8190 0.02383 0.01606 -0.0214 1.0000 0.0398 -8.500 -0.8063 0.02298 0.01520 -0.0200 1.0000 0.0415 -8.250 -0.7840 0.02183 0.01408 -0.0208 0.9553 0.0437 -8.000 -0.7524 0.02065 0.01282 -0.0231 0.9208 0.0483 -7.750 -0.7352 0.01957 0.01171 -0.0224 0.8988 0.0549 -7.500 -0.7235 0.01849 0.01069 -0.0206 0.8836 0.0691 -7.250 -0.7123 0.01741 0.00976 -0.0186 0.8718 0.0970 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0.6516 -2.250 -0.2453 0.01559 0.00922 -0.0018 0.7507 0.6569 -2.000 -0.2188 0.01565 0.00916 -0.0015 0.7468 0.6654 -1.750 -0.1906 0.01583 0.00939 -0.0013 0.7420 0.6696 -1.500 -0.1632 0.01595 0.00949 -0.0011 0.7374 0.6758 -1.250 -0.1361 0.01600 0.00948 -0.0009 0.7337 0.6817 -1.000 -0.1085 0.01612 0.00964 -0.0007 0.7287 0.6864 -0.750 -0.0816 0.01616 0.00960 -0.0006 0.7234 0.6937 -0.500 -0.0545 0.01624 0.00969 -0.0001 0.7189 0.6980 -0.250 -0.0273 0.01625 0.00972 -0.0001 0.7126 0.7035 0.000 0.0000 0.01623 0.00965 0.0000 0.7085 0.7085 0.250 0.0273 0.01625 0.00972 0.0001 0.7035 0.7126 0.500 0.0544 0.01624 0.00969 0.0001 0.6980 0.7189 0.750 0.0816 0.01616 0.00961 0.0006 0.6937 0.7235 1.000 0.1085 0.01613 0.00965 0.0007 0.6865 0.7288 1.250 0.1360 0.01600 0.00948 0.0009 0.6817 0.7337 1.500 0.1632 0.01595 0.00949 0.0011 0.6758 0.7374 1.750 0.1906 0.01583 0.00939 0.0013 0.6696 0.7420 2.000 0.2188 0.01565 0.00915 0.0015 0.6653 0.7468 2.250 0.2453 0.01559 0.00922 0.0018 0.6569 0.7507 2.500 0.2732 0.01541 0.00903 0.0021 0.6516 0.7558 2.750 0.3000 0.01531 0.00898 0.0024 0.6430 0.7611 3.000 0.3277 0.01497 0.00867 0.0030 0.6355 0.7660 3.250 0.3546 0.01479 0.00854 0.0033 0.6255 0.7719 3.500 0.3827 0.01449 0.00825 0.0037 0.6186 0.7766 3.750 0.4093 0.01427 0.00813 0.0042 0.6075 0.7815 4.000 0.4373 0.01389 0.00771 0.0047 0.5957 0.7868 4.250 0.4642 0.01352 0.00735 0.0054 0.5806 0.7911 4.500 0.4905 0.01325 0.00713 0.0061 0.5625 0.7960 4.750 0.5170 0.01306 0.00693 0.0066 0.5426 0.8015 5.000 0.5424 0.01291 0.00679 0.0074 0.5188 0.8063 5.250 0.5674 0.01283 0.00673 0.0081 0.4871 0.8124 5.500 0.5918 0.01288 0.00670 0.0088 0.4508 0.8184 5.750 0.6143 0.01306 0.00678 0.0099 0.4087 0.8245 6.000 0.6352 0.01347 0.00697 0.0109 0.3546 0.8317 6.250 0.6522 0.01408 0.00733 0.0125 0.2923 0.8384 6.500 0.6676 0.01491 0.00786 0.0140 0.2301 0.8465 6.750 0.6826 0.01571 0.00843 0.0156 0.1773 0.8538 7.000 0.6979 0.01656 0.00906 0.0170 0.1325 0.8625 7.250 0.7122 0.01743 0.00976 0.0186 0.0964 0.8718 7.500 0.7237 0.01849 0.01069 0.0206 0.0691 0.8836 7.750 0.7354 0.01957 0.01170 0.0224 0.0549 0.8989 8.000 0.7528 0.02063 0.01281 0.0231 0.0485 0.9207 8.250 0.7841 0.02185 0.01410 0.0208 0.0438 0.9554 8.500 0.8067 0.02297 0.01519 0.0199 0.0414 1.0000 8.750 0.8191 0.02385 0.01607 0.0213 0.0397 1.0000 9.000 0.8310 0.02481 0.01697 0.0227 0.0383 1.0000 9.250 0.8434 0.02598 0.01806 0.0239 0.0375 1.0000 9.500 0.8591 0.02704 0.01915 0.0250 0.0367 1.0000 9.750 0.8764 0.02812 0.02025 0.0259 0.0359 1.0000 10.000 0.8948 0.02922 0.02137 0.0267 0.0352 1.0000 10.250 0.9142 0.03037 0.02253 0.0274 0.0345 1.0000 10.500 0.9354 0.03156 0.02372 0.0279 0.0340 1.0000 10.750 0.9584 0.03284 0.02500 0.0283 0.0336 1.0000 11.000 0.9903 0.03458 0.02670 0.0277 0.0331 1.0000 11.250 1.0104 0.03627 0.02851 0.0282 0.0329 1.0000 11.500 1.0246 0.03801 0.03045 0.0292 0.0328 1.0000 11.750 1.0365 0.03998 0.03261 0.0303 0.0327 1.0000 12.000 1.0495 0.04203 0.03482 0.0311 0.0327 1.0000 12.250 1.0548 0.04433 0.03734 0.0324 0.0327 1.0000 12.500 1.0617 0.04674 0.03991 0.0333 0.0328 1.0000 12.750 1.0644 0.04937 0.04272 0.0343 0.0329 1.0000 13.000 1.0703 0.05225 0.04575 0.0350 0.0330 1.0000 13.250 1.0585 0.05487 0.04864 0.0360 0.0332 1.0000 13.500 0.9967 0.06132 0.05581 0.0361 0.0344 1.0000 13.750 0.9625 0.06767 0.06253 0.0347 0.0351 1.0000 14.000 0.9350 0.07378 0.06889 0.0324 0.0357 1.0000 14.250 0.9098 0.08012 0.07542 0.0294 0.0361 1.0000 14.500 0.8858 0.08689 0.08235 0.0259 0.0366 1.0000 14.750 0.8659 0.09371 0.08930 0.0222 0.0369 1.0000 15.000 0.8628 0.09850 0.09412 0.0202 0.0373 1.0000