EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 598 AIRFOIL (e598-il) Reynolds number: 50,000 Max Cl/Cd: 23.49 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e598-il-50000-n5.txt Download as CSV file: xf-e598-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3590 0.13110 0.12488 -0.0013 1.0000 0.0864
-10.250 -0.3578 0.12866 0.12252 -0.0042 1.0000 0.0875
-10.000 -0.3562 0.12599 0.11995 -0.0070 1.0000 0.0880
-9.750 -0.3525 0.12286 0.11691 -0.0097 1.0000 0.0881
-9.500 -0.3469 0.11947 0.11361 -0.0120 1.0000 0.0882
-9.250 -0.3410 0.11589 0.11011 -0.0145 1.0000 0.0883
-9.000 -0.3313 0.11195 0.10626 -0.0164 1.0000 0.0881
-8.750 -0.3129 0.10351 0.09779 -0.0175 1.0000 0.0551
-8.500 -0.3048 0.09981 0.09419 -0.0199 1.0000 0.0542
-8.250 -0.2963 0.09609 0.09057 -0.0233 0.9439 0.0532
-8.000 -0.2826 0.09168 0.08609 -0.0284 0.8935 0.0523
-7.500 -0.2841 0.08303 0.07732 -0.0372 0.8417 0.0485
-7.250 -0.2799 0.07931 0.07352 -0.0399 0.8245 0.0484
-7.000 -0.2740 0.07568 0.06981 -0.0421 0.8102 0.0482
-6.750 -0.2674 0.07181 0.06585 -0.0446 0.7978 0.0479
-6.500 -0.2589 0.06770 0.06164 -0.0474 0.7860 0.0476
-6.250 -0.2495 0.06332 0.05712 -0.0502 0.7759 0.0474
-6.000 -0.2389 0.05862 0.05221 -0.0530 0.7666 0.0474
-5.750 -0.2267 0.05314 0.04639 -0.0562 0.7576 0.0481
-5.500 -0.2109 0.05042 0.04347 -0.0567 0.7492 0.0504
-5.250 -0.1931 0.04691 0.03963 -0.0580 0.7403 0.0530
-5.000 -0.1753 0.04230 0.03439 -0.0590 0.7334 0.0550
-4.750 -0.1542 0.03962 0.03134 -0.0593 0.7251 0.0590
-4.500 -0.1321 0.03674 0.02785 -0.0592 0.7179 0.0644
-4.250 -0.1086 0.03510 0.02594 -0.0591 0.7102 0.0709
-4.000 -0.0840 0.03308 0.02340 -0.0588 0.7031 0.0789
-3.750 -0.0584 0.03150 0.02132 -0.0582 0.6967 0.0889
-3.500 -0.0327 0.03053 0.02017 -0.0581 0.6889 0.0994
-3.250 -0.0071 0.02955 0.01897 -0.0574 0.6830 0.1107
-3.000 0.0198 0.02871 0.01792 -0.0574 0.6757 0.1232
-2.750 0.0468 0.02794 0.01693 -0.0570 0.6694 0.1368
-2.500 0.0744 0.02728 0.01606 -0.0566 0.6636 0.1516
-2.250 0.1030 0.02680 0.01545 -0.0568 0.6564 0.1679
-2.000 0.1310 0.02632 0.01484 -0.0565 0.6510 0.1862
-1.750 0.1585 0.02599 0.01445 -0.0565 0.6447 0.2073
-1.500 0.1855 0.02569 0.01409 -0.0563 0.6382 0.2326
-1.250 0.2116 0.02530 0.01369 -0.0557 0.6334 0.2649
-1.000 0.2368 0.02499 0.01361 -0.0557 0.6269 0.3109
-0.500 0.3226 0.02273 0.01297 -0.0599 0.6160 1.0000
-0.250 0.3474 0.02325 0.01323 -0.0599 0.6090 1.0000
0.000 0.3720 0.02362 0.01331 -0.0593 0.6034 1.0000
0.250 0.3969 0.02387 0.01326 -0.0584 0.5991 1.0000
0.500 0.4207 0.02451 0.01377 -0.0584 0.5919 1.0000
0.750 0.4451 0.02491 0.01397 -0.0579 0.5865 1.0000
1.000 0.4701 0.02517 0.01401 -0.0570 0.5825 1.0000
1.250 0.4929 0.02595 0.01472 -0.0570 0.5749 1.0000
1.500 0.5172 0.02638 0.01501 -0.0565 0.5697 1.0000
1.750 0.5424 0.02664 0.01509 -0.0556 0.5659 1.0000
2.000 0.5639 0.02758 0.01603 -0.0557 0.5580 1.0000
2.250 0.5880 0.02803 0.01638 -0.0550 0.5529 1.0000
2.500 0.6134 0.02829 0.01650 -0.0542 0.5492 1.0000
2.750 0.6330 0.02943 0.01769 -0.0543 0.5409 1.0000
3.000 0.6572 0.02986 0.01805 -0.0536 0.5360 1.0000
3.250 0.6809 0.03038 0.01852 -0.0530 0.5313 1.0000
3.500 0.6998 0.03151 0.01970 -0.0528 0.5235 1.0000
3.750 0.7244 0.03187 0.02000 -0.0521 0.5189 1.0000
4.000 0.7440 0.03288 0.02104 -0.0517 0.5125 1.0000
4.250 0.7638 0.03381 0.02202 -0.0512 0.5058 1.0000
4.500 0.7896 0.03404 0.02221 -0.0504 0.5018 1.0000
4.750 0.8028 0.03571 0.02398 -0.0502 0.4934 1.0000
5.000 0.8251 0.03630 0.02458 -0.0495 0.4880 1.0000
5.250 0.8528 0.03631 0.02459 -0.0486 0.4845 1.0000
5.500 0.8583 0.03869 0.02712 -0.0483 0.4744 1.0000
5.750 0.8841 0.03887 0.02731 -0.0475 0.4702 1.0000
6.250 0.9115 0.04169 0.03032 -0.0462 0.4557 1.0000
6.500 0.9388 0.04170 0.03036 -0.0453 0.4519 1.0000
6.750 0.9345 0.04479 0.03359 -0.0447 0.4409 1.0000
7.000 0.9647 0.04447 0.03332 -0.0438 0.4376 1.0000
7.250 0.9521 0.04828 0.03724 -0.0432 0.4257 1.0000
7.500 0.9827 0.04785 0.03690 -0.0422 0.4224 1.0000
8.000 0.9736 0.05374 0.04293 -0.0408 0.4038 1.0000
8.500 0.9947 0.05673 0.04607 -0.0393 0.3901 1.0000
9.000 0.9626 0.06616 0.05559 -0.0402 0.3666 1.0000
9.250 0.9891 0.06581 0.05538 -0.0389 0.3624 1.0000
9.750 1.0021 0.06997 0.05972 -0.0382 0.3469 1.0000
10.250 1.0156 0.07409 0.06405 -0.0375 0.3314 1.0000
10.500 0.9987 0.07943 0.06943 -0.0387 0.3195 1.0000
10.750 1.0303 0.07806 0.06823 -0.0369 0.3160 1.0000
11.000 1.0122 0.08371 0.07392 -0.0383 0.3037 1.0000
11.500 1.0255 0.08804 0.07847 -0.0380 0.2881 1.0000
12.000 1.0400 0.09215 0.08282 -0.0377 0.2725 1.0000
12.500 1.0559 0.09592 0.08684 -0.0373 0.2571 1.0000
12.750 1.0349 0.10295 0.09390 -0.0398 0.2452 1.0000
13.250 1.0475 0.10749 0.09870 -0.0400 0.2296 1.0000
13.750 1.0613 0.11172 0.10317 -0.0402 0.2143 1.0000
14.250 1.0585 0.11946 0.11109 -0.0425 0.1975 1.0000
15.250 1.0370 0.13973 0.13166 -0.0504 0.1644 1.0000
15.500 1.0609 0.13796 0.13007 -0.0487 0.1588 1.0000
16.000 1.0631 0.14556 0.13784 -0.0516 0.1451 1.0000
16.500 1.0605 0.15473 0.14713 -0.0558 0.1319 1.0000
16.750 1.0360 0.16598 0.15831 -0.0620 0.1245 1.0000
17.000 1.0537 0.16553 0.15804 -0.0611 0.1195 1.0000
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Polar data table (+)
Polar graphs
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