XFOIL Version 6.96 Calculated polar for: SD7084 (9.6%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.4184 0.09178 0.08701 -0.0283 1.0000 0.1111 -8.250 -0.4454 0.08922 0.08463 -0.0335 1.0000 0.1140 -8.000 -0.4790 0.08626 0.08176 -0.0394 1.0000 0.1147 -7.750 -0.4305 0.08218 0.07765 -0.0300 1.0000 0.1204 -7.500 -0.4408 0.07956 0.07513 -0.0300 1.0000 0.1241 -7.250 -0.4759 0.07638 0.07197 -0.0361 1.0000 0.1283 -7.000 -0.4725 0.07250 0.06816 -0.0337 1.0000 0.1309 -6.750 -0.4638 0.07028 0.06600 -0.0301 1.0000 0.1356 -6.500 -0.4906 0.06690 0.06242 -0.0338 1.0000 0.1437 -6.250 -0.4749 0.06415 0.05986 -0.0291 1.0000 0.1479 -6.000 -0.4845 0.06098 0.05650 -0.0304 1.0000 0.1585 -5.750 -0.4736 0.05891 0.05456 -0.0268 1.0000 0.1674 -5.500 -0.4705 0.05618 0.05181 -0.0252 1.0000 0.1783 -5.250 -0.4664 0.05342 0.04899 -0.0242 1.0000 0.1912 -5.000 -0.4600 0.05079 0.04630 -0.0230 1.0000 0.2051 -4.750 -0.4298 0.03519 0.02859 -0.0288 1.0000 0.0826 -4.500 -0.4094 0.03135 0.02381 -0.0270 1.0000 0.0721 -4.250 -0.3897 0.02863 0.02076 -0.0258 1.0000 0.0706 -4.000 -0.3685 0.02653 0.01827 -0.0246 1.0000 0.0701 -3.750 -0.3466 0.02536 0.01664 -0.0233 1.0000 0.0728 -3.500 -0.3236 0.02349 0.01450 -0.0223 1.0000 0.0745 -3.250 -0.3011 0.02203 0.01297 -0.0214 1.0000 0.0766 -3.000 -0.2791 0.02100 0.01188 -0.0203 1.0000 0.0801 -2.750 -0.2574 0.02020 0.01096 -0.0192 1.0000 0.0858 -2.500 -0.2373 0.01936 0.01024 -0.0181 1.0000 0.0969 -2.250 -0.2171 0.01855 0.00948 -0.0169 1.0000 0.1143 -2.000 -0.1968 0.01722 0.00874 -0.0160 0.9997 0.1895 -1.750 -0.1402 0.01445 0.00906 -0.0195 0.9998 1.0000 -1.500 -0.0882 0.01493 0.00908 -0.0250 0.9898 1.0000 -1.250 -0.0376 0.01539 0.00919 -0.0301 0.9796 1.0000 -1.000 0.0141 0.01581 0.00934 -0.0353 0.9696 1.0000 -0.750 0.0628 0.01609 0.00938 -0.0398 0.9581 1.0000 -0.500 0.1088 0.01629 0.00941 -0.0437 0.9459 1.0000 -0.250 0.1547 0.01642 0.00939 -0.0473 0.9335 1.0000 0.000 0.2015 0.01648 0.00934 -0.0510 0.9213 1.0000 0.250 0.2517 0.01642 0.00920 -0.0552 0.9097 1.0000 0.500 0.3099 0.01617 0.00888 -0.0607 0.9007 1.0000 0.750 0.3514 0.01593 0.00860 -0.0628 0.8871 1.0000 1.000 0.3898 0.01566 0.00830 -0.0641 0.8730 1.0000 1.250 0.4253 0.01534 0.00797 -0.0647 0.8584 1.0000 1.500 0.4568 0.01504 0.00764 -0.0644 0.8425 1.0000 1.750 0.4827 0.01482 0.00740 -0.0632 0.8233 1.0000 2.000 0.5109 0.01454 0.00710 -0.0622 0.8051 1.0000 2.250 0.5396 0.01423 0.00675 -0.0612 0.7869 1.0000 2.500 0.5635 0.01412 0.00660 -0.0596 0.7637 1.0000 2.750 0.5895 0.01400 0.00642 -0.0583 0.7413 1.0000 3.000 0.6145 0.01396 0.00630 -0.0569 0.7165 1.0000 3.250 0.6384 0.01405 0.00630 -0.0555 0.6897 1.0000 3.500 0.6621 0.01420 0.00635 -0.0541 0.6621 1.0000 3.750 0.6856 0.01442 0.00649 -0.0527 0.6341 1.0000 4.000 0.7089 0.01469 0.00665 -0.0514 0.6058 1.0000 4.250 0.7319 0.01502 0.00687 -0.0501 0.5779 1.0000 4.500 0.7548 0.01540 0.00714 -0.0489 0.5504 1.0000 4.750 0.7777 0.01581 0.00748 -0.0477 0.5240 1.0000 5.000 0.8007 0.01626 0.00781 -0.0466 0.4991 1.0000 5.250 0.8233 0.01674 0.00823 -0.0455 0.4744 1.0000 5.500 0.8459 0.01725 0.00870 -0.0444 0.4511 1.0000 5.750 0.8690 0.01780 0.00915 -0.0435 0.4299 1.0000 6.000 0.8914 0.01835 0.00975 -0.0424 0.4086 1.0000 6.250 0.9142 0.01893 0.01030 -0.0415 0.3890 1.0000 6.500 0.9371 0.01955 0.01086 -0.0406 0.3705 1.0000 6.750 0.9590 0.02016 0.01155 -0.0396 0.3516 1.0000 7.000 0.9810 0.02079 0.01223 -0.0385 0.3334 1.0000 7.250 1.0032 0.02144 0.01287 -0.0376 0.3160 1.0000 7.500 1.0244 0.02212 0.01359 -0.0365 0.2984 1.0000 7.750 1.0444 0.02276 0.01435 -0.0352 0.2799 1.0000 8.000 1.0640 0.02339 0.01502 -0.0339 0.2614 1.0000 8.250 1.0827 0.02403 0.01567 -0.0325 0.2426 1.0000 8.500 1.0980 0.02454 0.01635 -0.0306 0.2213 1.0000 8.750 1.1114 0.02501 0.01685 -0.0286 0.1991 1.0000 9.000 1.1213 0.02549 0.01735 -0.0261 0.1735 1.0000 9.250 1.1283 0.02620 0.01816 -0.0233 0.1407 1.0000 9.500 1.1292 0.02783 0.01959 -0.0200 0.1012 1.0000 9.750 1.1275 0.03012 0.02167 -0.0164 0.0743 1.0000 10.000 1.1277 0.03214 0.02363 -0.0130 0.0615 1.0000 10.250 1.1306 0.03433 0.02583 -0.0100 0.0540 1.0000 10.500 1.1375 0.03642 0.02796 -0.0077 0.0489 1.0000 10.750 1.1525 0.03937 0.03096 -0.0064 0.0453 1.0000 11.000 1.1637 0.04168 0.03354 -0.0046 0.0424 1.0000 11.250 1.1708 0.04387 0.03590 -0.0028 0.0399 1.0000 11.500 1.1795 0.04639 0.03848 -0.0015 0.0378 1.0000 11.750 1.1905 0.05117 0.04342 -0.0008 0.0362 1.0000 12.000 1.1871 0.05415 0.04673 0.0013 0.0359 1.0000 12.250 1.1794 0.05743 0.05032 0.0033 0.0357 1.0000 12.500 1.1688 0.06101 0.05420 0.0047 0.0357 1.0000 12.750 1.1561 0.06490 0.05836 0.0055 0.0357 1.0000 13.000 1.1398 0.06929 0.06301 0.0055 0.0357 1.0000 13.250 1.1234 0.07415 0.06810 0.0048 0.0359 1.0000 13.500 1.1049 0.07952 0.07369 0.0031 0.0360 1.0000 13.750 1.0854 0.08553 0.07989 0.0006 0.0361 1.0000 14.000 1.0677 0.09150 0.08608 -0.0025 0.0364 1.0000 14.250 1.0457 0.09825 0.09303 -0.0072 0.0367 1.0000 14.500 0.9999 0.11099 0.10610 -0.0177 0.0382 1.0000 14.750 0.9156 0.13901 0.13419 -0.0362 0.0453 1.0000 15.000 0.9060 0.14734 0.14249 -0.0400 0.0461 1.0000