EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 598 AIRFOIL (e598-il) Reynolds number: 100,000 Max Cl/Cd: 43.26 at α=11.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e598-il-100000.txt Download as CSV file: xf-e598-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 598 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2705 0.09633 0.09245 -0.0247 0.8950 0.0850
-8.000 -0.2779 0.09474 0.09079 -0.0287 0.8657 0.0875
-7.750 -0.2906 0.09328 0.08929 -0.0331 0.8451 0.0881
-7.500 -0.2693 0.08801 0.08396 -0.0298 0.8317 0.0905
-7.250 -0.2560 0.08516 0.08107 -0.0288 0.8180 0.0945
-7.000 -0.2564 0.08279 0.07869 -0.0305 0.8058 0.0979
-6.750 -0.2658 0.08074 0.07654 -0.0411 0.7953 0.1013
-6.500 -0.2568 0.07611 0.07192 -0.0416 0.7856 0.1030
-6.250 -0.2419 0.07303 0.06883 -0.0385 0.7767 0.1057
-6.000 -0.2302 0.07011 0.06585 -0.0398 0.7680 0.1095
-5.750 -0.2223 0.06633 0.06177 -0.0503 0.7607 0.1169
-5.500 -0.2074 0.06261 0.05814 -0.0479 0.7528 0.1190
-5.250 -0.1921 0.05974 0.05520 -0.0476 0.7460 0.1232
-5.000 -0.1717 0.04374 0.03786 -0.0591 0.7425 0.0658
-4.750 -0.1516 0.04368 0.03811 -0.0579 0.7346 0.0731
-4.500 -0.1313 0.03866 0.03260 -0.0588 0.7288 0.0703
-4.250 -0.1087 0.03418 0.02749 -0.0591 0.7222 0.0704
-4.000 -0.0853 0.03086 0.02340 -0.0583 0.7169 0.0746
-3.750 -0.0601 0.02929 0.02162 -0.0581 0.7099 0.0832
-3.500 -0.0347 0.02783 0.01985 -0.0576 0.7033 0.0945
-3.250 -0.0095 0.02663 0.01830 -0.0567 0.6984 0.1072
-3.000 0.0181 0.02562 0.01705 -0.0568 0.6911 0.1205
-2.750 0.0446 0.02476 0.01593 -0.0561 0.6852 0.1341
-2.500 0.0714 0.02420 0.01516 -0.0557 0.6796 0.1485
-2.250 0.0988 0.02367 0.01456 -0.0557 0.6729 0.1637
-2.000 0.1252 0.02306 0.01387 -0.0551 0.6678 0.1798
-1.750 0.1522 0.02268 0.01345 -0.0549 0.6619 0.1977
-1.500 0.1789 0.02222 0.01310 -0.0548 0.6555 0.2178
-1.250 0.2049 0.02181 0.01273 -0.0541 0.6508 0.2425
-1.000 0.2310 0.02157 0.01264 -0.0539 0.6448 0.2743
-0.750 0.2567 0.02117 0.01250 -0.0536 0.6386 0.3242
-0.500 0.3282 0.01872 0.01180 -0.0605 0.6334 1.0000
-0.250 0.3539 0.01926 0.01213 -0.0606 0.6269 1.0000
0.000 0.3788 0.01962 0.01228 -0.0600 0.6210 1.0000
0.250 0.4035 0.01985 0.01227 -0.0590 0.6167 1.0000
0.500 0.4283 0.02051 0.01285 -0.0591 0.6101 1.0000
0.750 0.4531 0.02091 0.01311 -0.0586 0.6042 1.0000
1.000 0.4780 0.02112 0.01313 -0.0576 0.6001 1.0000
1.250 0.5021 0.02190 0.01390 -0.0578 0.5932 1.0000
1.500 0.5267 0.02234 0.01424 -0.0573 0.5874 1.0000
1.750 0.5521 0.02251 0.01425 -0.0563 0.5835 1.0000
2.000 0.5751 0.02346 0.01523 -0.0565 0.5761 1.0000
2.250 0.5996 0.02391 0.01561 -0.0560 0.5706 1.0000
2.500 0.6255 0.02402 0.01558 -0.0550 0.5669 1.0000
2.750 0.6469 0.02519 0.01683 -0.0553 0.5588 1.0000
3.000 0.6716 0.02558 0.01717 -0.0546 0.5535 1.0000
3.250 0.6983 0.02561 0.01708 -0.0536 0.5501 1.0000
3.500 0.7173 0.02708 0.01868 -0.0540 0.5411 1.0000
3.750 0.7427 0.02732 0.01886 -0.0532 0.5364 1.0000
4.000 0.7705 0.02723 0.01866 -0.0522 0.5333 1.0000
4.250 0.7862 0.02905 0.02067 -0.0525 0.5233 1.0000
4.500 0.8132 0.02905 0.02061 -0.0516 0.5192 1.0000
4.750 0.8332 0.03015 0.02177 -0.0513 0.5124 1.0000
5.000 0.8543 0.03099 0.02267 -0.0509 0.5054 1.0000
5.250 0.8837 0.03067 0.02230 -0.0499 0.5021 1.0000
5.500 0.8953 0.03281 0.02461 -0.0499 0.4923 1.0000
5.750 0.9226 0.03273 0.02452 -0.0490 0.4878 1.0000
6.000 0.9548 0.03209 0.02382 -0.0481 0.4850 1.0000
6.250 0.9600 0.03482 0.02678 -0.0479 0.4737 1.0000
6.500 0.9929 0.03404 0.02597 -0.0470 0.4704 1.0000
6.750 0.9975 0.03673 0.02884 -0.0466 0.4600 1.0000
7.000 1.0291 0.03605 0.02818 -0.0457 0.4559 1.0000
7.250 1.0665 0.03478 0.02686 -0.0448 0.4532 1.0000
7.500 1.0646 0.03792 0.03023 -0.0442 0.4414 1.0000
7.750 1.1052 0.03622 0.02852 -0.0433 0.4386 1.0000
8.000 1.1013 0.03941 0.03192 -0.0425 0.4272 1.0000
8.250 1.1454 0.03727 0.02977 -0.0416 0.4240 1.0000
8.500 1.1435 0.04003 0.03274 -0.0405 0.4135 1.0000
8.750 1.1887 0.03773 0.03044 -0.0398 0.4094 1.0000
9.000 1.2059 0.03836 0.03119 -0.0387 0.4016 1.0000
9.250 1.2376 0.03739 0.03029 -0.0379 0.3947 1.0000
9.500 1.2713 0.03629 0.02923 -0.0372 0.3881 1.0000
9.750 1.2935 0.03618 0.02924 -0.0362 0.3792 1.0000
10.000 1.3154 0.03613 0.02930 -0.0351 0.3705 1.0000
10.250 1.3564 0.03424 0.02738 -0.0347 0.3622 1.0000
10.500 1.3668 0.03506 0.02840 -0.0331 0.3513 1.0000
10.750 1.3940 0.03438 0.02776 -0.0322 0.3409 1.0000
11.000 1.4277 0.03319 0.02650 -0.0316 0.3296 1.0000
11.250 1.4432 0.03336 0.02678 -0.0301 0.3170 1.0000
11.500 1.4519 0.03399 0.02754 -0.0282 0.3042 1.0000
11.750 1.4603 0.03458 0.02822 -0.0262 0.2912 1.0000
12.000 1.4654 0.03531 0.02899 -0.0240 0.2784 1.0000
12.250 1.4664 0.03622 0.02992 -0.0216 0.2660 1.0000
12.500 1.4661 0.03741 0.03109 -0.0195 0.2534 1.0000
12.750 1.4649 0.03891 0.03257 -0.0179 0.2406 1.0000
13.000 1.4596 0.04094 0.03459 -0.0167 0.2282 1.0000
13.250 1.4464 0.04402 0.03777 -0.0161 0.2169 1.0000
13.500 1.4379 0.04692 0.04070 -0.0156 0.2051 1.0000
13.750 1.4311 0.04979 0.04355 -0.0154 0.1935 1.0000
14.000 1.4260 0.05262 0.04633 -0.0151 0.1818 1.0000
14.250 1.4229 0.05529 0.04890 -0.0149 0.1703 1.0000
14.500 1.4107 0.05922 0.05293 -0.0154 0.1608 1.0000
14.750 1.4024 0.06285 0.05660 -0.0157 0.1513 1.0000
15.000 1.3996 0.06582 0.05949 -0.0158 0.1415 1.0000
15.250 1.3968 0.06886 0.06249 -0.0160 0.1322 1.0000
15.500 1.3852 0.07339 0.06718 -0.0170 0.1251 1.0000
15.750 1.3865 0.07611 0.06980 -0.0171 0.1163 1.0000
16.000 1.3762 0.08067 0.07451 -0.0183 0.1102 1.0000
16.250 1.3754 0.08394 0.07776 -0.0188 0.1031 1.0000
16.500 1.3682 0.08827 0.08221 -0.0201 0.0975 1.0000
16.750 1.3679 0.09163 0.08557 -0.0205 0.0916 1.0000
17.000 1.3553 0.09705 0.09120 -0.0226 0.0876 1.0000
17.250 1.0497 0.17311 0.16793 -0.0651 0.1154 1.0000
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