XFOIL Version 6.96 Calculated polar for: EPPLER 330 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5342 0.08691 0.08486 0.0006 0.7850 0.0051 -9.000 -0.5457 0.08121 0.07907 -0.0041 0.7559 0.0051 -8.750 -0.5591 0.07642 0.07418 -0.0066 0.7333 0.0051 -6.250 -0.5991 0.03267 0.02849 0.0165 0.6009 0.0029 -6.000 -0.5976 0.02540 0.02062 0.0220 0.5942 0.0028 -5.750 -0.5867 0.02006 0.01460 0.0260 0.5844 0.0026 -5.500 -0.5661 0.01736 0.01142 0.0279 0.5734 0.0026 -5.250 -0.5421 0.01591 0.00970 0.0289 0.5617 0.0026 -5.000 -0.5175 0.01468 0.00823 0.0297 0.5505 0.0026 -4.750 -0.4926 0.01382 0.00721 0.0305 0.5391 0.0026 -4.500 -0.4678 0.01312 0.00636 0.0312 0.5279 0.0026 -4.250 -0.4433 0.01247 0.00557 0.0321 0.5176 0.0027 -4.000 -0.4184 0.01201 0.00501 0.0328 0.5075 0.0027 -3.750 -0.3936 0.01158 0.00449 0.0335 0.4977 0.0028 -3.500 -0.3687 0.01121 0.00403 0.0342 0.4876 0.0029 -3.250 -0.3434 0.01090 0.00365 0.0348 0.4783 0.0030 -3.000 -0.3178 0.01066 0.00336 0.0354 0.4693 0.0031 -2.750 -0.2931 0.01031 0.00293 0.0361 0.4607 0.0037 -2.500 -0.2672 0.01013 0.00271 0.0366 0.4522 0.0041 -2.250 -0.2412 0.00998 0.00251 0.0371 0.4441 0.0047 -2.000 -0.2150 0.00983 0.00231 0.0375 0.4357 0.0050 -1.750 -0.1889 0.00969 0.00214 0.0379 0.4279 0.0063 -1.500 -0.1626 0.00956 0.00199 0.0383 0.4204 0.0089 -1.250 -0.1370 0.00937 0.00185 0.0388 0.4139 0.0247 -1.000 -0.1117 0.00917 0.00174 0.0393 0.4060 0.0553 -0.750 -0.0879 0.00885 0.00165 0.0401 0.3997 0.1302 -0.500 -0.0622 0.00869 0.00157 0.0405 0.3935 0.1692 -0.250 -0.0407 0.00823 0.00145 0.0417 0.3873 0.2860 0.000 -0.0600 0.00587 0.00115 0.0513 0.3846 0.8314 0.250 -0.0350 0.00595 0.00133 0.0523 0.3782 0.8897 0.500 -0.0088 0.00605 0.00138 0.0529 0.3723 0.9026 0.750 0.0190 0.00614 0.00145 0.0531 0.3671 0.9097 1.000 0.0454 0.00625 0.00150 0.0535 0.3606 0.9172 1.250 0.0740 0.00635 0.00156 0.0535 0.3553 0.9205 1.500 0.1020 0.00643 0.00160 0.0535 0.3500 0.9235 2.000 0.1560 0.00655 0.00163 0.0539 0.3392 0.9281 2.250 0.1829 0.00661 0.00165 0.0541 0.3340 0.9297 2.500 0.2116 0.00668 0.00168 0.0539 0.3290 0.9308 2.750 0.2401 0.00674 0.00173 0.0538 0.3236 0.9320 3.000 0.2682 0.00683 0.00178 0.0537 0.3183 0.9332 3.250 0.2963 0.00690 0.00183 0.0536 0.3133 0.9343 3.500 0.3243 0.00697 0.00189 0.0535 0.3081 0.9354 3.750 0.3519 0.00708 0.00196 0.0535 0.3024 0.9372 4.000 0.3795 0.00715 0.00203 0.0535 0.2975 0.9386 4.250 0.4065 0.00724 0.00209 0.0536 0.2918 0.9402 4.500 0.4332 0.00733 0.00216 0.0537 0.2861 0.9417 4.750 0.4595 0.00741 0.00225 0.0540 0.2806 0.9434 5.000 0.4871 0.00753 0.00234 0.0539 0.2741 0.9448 5.250 0.5155 0.00764 0.00247 0.0537 0.2684 0.9467 5.500 0.5430 0.00776 0.00257 0.0536 0.2616 0.9475 5.750 0.5705 0.00787 0.00269 0.0535 0.2549 0.9483 6.000 0.5977 0.00801 0.00280 0.0535 0.2474 0.9491 6.250 0.6248 0.00814 0.00293 0.0534 0.2394 0.9500 6.500 0.6514 0.00830 0.00308 0.0535 0.2312 0.9510 6.750 0.6782 0.00844 0.00322 0.0535 0.2235 0.9520 7.000 0.7043 0.00861 0.00338 0.0536 0.2143 0.9531 7.250 0.7299 0.00882 0.00355 0.0538 0.2040 0.9543 7.500 0.7553 0.00901 0.00374 0.0540 0.1934 0.9555 7.750 0.7797 0.00925 0.00395 0.0543 0.1808 0.9570 8.000 0.8044 0.00949 0.00417 0.0546 0.1699 0.9583 8.250 0.8300 0.00982 0.00445 0.0547 0.1546 0.9593 8.500 0.8551 0.01017 0.00477 0.0547 0.1397 0.9603 8.750 0.8796 0.01056 0.00511 0.0549 0.1252 0.9615 9.000 0.9041 0.01093 0.00545 0.0550 0.1131 0.9627 9.250 0.9274 0.01138 0.00585 0.0553 0.0983 0.9642 9.500 0.9499 0.01187 0.00629 0.0557 0.0831 0.9659 9.750 0.9717 0.01236 0.00675 0.0563 0.0707 0.9679 10.000 0.9927 0.01281 0.00718 0.0570 0.0619 0.9701 10.250 1.0128 0.01328 0.00764 0.0578 0.0537 0.9723 10.500 1.0374 0.01380 0.00816 0.0576 0.0455 0.9735 10.750 1.0618 0.01435 0.00871 0.0574 0.0390 0.9748 11.000 1.0837 0.01508 0.00940 0.0573 0.0296 0.9766 11.250 1.1050 0.01582 0.01013 0.0574 0.0225 0.9787 11.500 1.1240 0.01665 0.01094 0.0577 0.0157 0.9812 11.750 1.1425 0.01724 0.01158 0.0584 0.0141 0.9842 12.000 1.1638 0.01817 0.01251 0.0578 0.0099 0.9855 12.250 1.1877 0.01893 0.01334 0.0570 0.0092 0.9866 12.500 1.2062 0.01997 0.01441 0.0566 0.0069 0.9885 12.750 1.2232 0.02102 0.01553 0.0562 0.0059 0.9910 13.000 1.2375 0.02229 0.01687 0.0556 0.0052 0.9941 13.250 1.2518 0.02395 0.01862 0.0540 0.0042 0.9969 13.500 1.2654 0.02605 0.02081 0.0517 0.0035 0.9992 13.750 1.2687 0.02830 0.02314 0.0510 0.0030 1.0000 14.000 1.2627 0.03062 0.02555 0.0520 0.0028 1.0000 14.250 1.2571 0.03333 0.02833 0.0523 0.0025 1.0000 14.500 1.2506 0.03641 0.03150 0.0520 0.0021 1.0000 14.750 1.2429 0.03980 0.03497 0.0515 0.0017 1.0000 15.250 1.2282 0.04681 0.04216 0.0500 0.0016 1.0000 15.500 1.2213 0.05034 0.04577 0.0491 0.0016 1.0000 15.750 1.2127 0.05416 0.04968 0.0480 0.0015 1.0000 16.000 1.2021 0.05829 0.05390 0.0468 0.0015 1.0000 16.250 1.1926 0.06245 0.05816 0.0454 0.0014 1.0000 16.500 1.1775 0.06752 0.06331 0.0435 0.0011 1.0000 16.750 1.1717 0.07143 0.06731 0.0421 0.0013 1.0000 17.000 1.1577 0.07660 0.07256 0.0401 0.0010 1.0000