EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 598 AIRFOIL (e598-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.35 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e598-il-1000000-n5.txt Download as CSV file: xf-e598-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6226 0.05185 0.04882 -0.0340 0.5902 0.0038
-9.250 -0.6679 0.02760 0.02362 -0.0454 0.5914 0.0037
-9.000 -0.6508 0.02473 0.02042 -0.0455 0.5851 0.0037
-8.750 -0.6308 0.02264 0.01805 -0.0454 0.5798 0.0037
-8.500 -0.6093 0.02094 0.01610 -0.0451 0.5739 0.0037
-8.250 -0.5863 0.01959 0.01452 -0.0448 0.5677 0.0037
-8.000 -0.5624 0.01841 0.01315 -0.0444 0.5624 0.0037
-7.750 -0.5377 0.01741 0.01196 -0.0441 0.5569 0.0037
-7.500 -0.5125 0.01652 0.01090 -0.0437 0.5518 0.0038
-7.250 -0.4869 0.01572 0.00995 -0.0434 0.5473 0.0038
-7.000 -0.4608 0.01501 0.00911 -0.0431 0.5425 0.0038
-6.750 -0.4344 0.01438 0.00834 -0.0428 0.5374 0.0038
-6.500 -0.4077 0.01382 0.00765 -0.0425 0.5328 0.0038
-6.250 -0.3808 0.01325 0.00699 -0.0423 0.5292 0.0039
-6.000 -0.3540 0.01266 0.00628 -0.0420 0.5249 0.0039
-5.750 -0.3268 0.01214 0.00564 -0.0417 0.5204 0.0040
-5.500 -0.2994 0.01172 0.00513 -0.0415 0.5162 0.0042
-5.250 -0.2718 0.01133 0.00468 -0.0413 0.5130 0.0043
-5.000 -0.2439 0.01102 0.00430 -0.0411 0.5093 0.0045
-4.750 -0.2160 0.01074 0.00395 -0.0409 0.5052 0.0048
-4.500 -0.1880 0.01050 0.00365 -0.0407 0.5012 0.0051
-4.250 -0.1599 0.01026 0.00336 -0.0406 0.4981 0.0055
-4.000 -0.1318 0.01001 0.00308 -0.0404 0.4949 0.0063
-3.750 -0.1037 0.00980 0.00283 -0.0402 0.4912 0.0076
-3.500 -0.0756 0.00960 0.00260 -0.0401 0.4873 0.0100
-3.250 -0.0475 0.00940 0.00240 -0.0400 0.4840 0.0146
-3.000 -0.0192 0.00921 0.00223 -0.0399 0.4812 0.0200
-2.750 0.0091 0.00906 0.00208 -0.0398 0.4778 0.0258
-2.500 0.0373 0.00892 0.00195 -0.0397 0.4741 0.0324
-2.250 0.0656 0.00879 0.00184 -0.0396 0.4707 0.0419
-2.000 0.0938 0.00865 0.00175 -0.0395 0.4675 0.0551
-1.750 0.1223 0.00854 0.00167 -0.0395 0.4644 0.0644
-1.500 0.1507 0.00845 0.00159 -0.0394 0.4609 0.0724
-1.250 0.1792 0.00839 0.00152 -0.0394 0.4574 0.0800
-1.000 0.2077 0.00834 0.00147 -0.0393 0.4538 0.0884
-0.750 0.2362 0.00827 0.00142 -0.0393 0.4506 0.0989
-0.500 0.2648 0.00821 0.00138 -0.0393 0.4474 0.1083
-0.250 0.2933 0.00817 0.00135 -0.0393 0.4437 0.1181
0.000 0.3218 0.00813 0.00132 -0.0393 0.4397 0.1299
0.250 0.3502 0.00810 0.00130 -0.0393 0.4362 0.1441
0.500 0.3788 0.00804 0.00129 -0.0393 0.4329 0.1610
1.000 0.4355 0.00794 0.00130 -0.0393 0.4248 0.2110
1.250 0.4637 0.00789 0.00132 -0.0393 0.4209 0.2463
1.500 0.4919 0.00779 0.00134 -0.0393 0.4172 0.2956
1.750 0.5195 0.00760 0.00137 -0.0393 0.4130 0.3854
2.250 0.5894 0.00624 0.00155 -0.0423 0.4041 0.9935
2.500 0.6311 0.00629 0.00156 -0.0452 0.3992 0.9991
2.750 0.6609 0.00637 0.00160 -0.0456 0.3943 1.0000
3.000 0.6878 0.00647 0.00166 -0.0453 0.3898 1.0000
3.250 0.7148 0.00654 0.00171 -0.0451 0.3855 1.0000
3.500 0.7417 0.00663 0.00178 -0.0448 0.3802 1.0000
3.750 0.7685 0.00675 0.00185 -0.0445 0.3751 1.0000
4.000 0.7955 0.00683 0.00193 -0.0443 0.3704 1.0000
4.250 0.8223 0.00694 0.00202 -0.0441 0.3648 1.0000
4.500 0.8491 0.00707 0.00212 -0.0439 0.3597 1.0000
4.750 0.8760 0.00717 0.00222 -0.0436 0.3542 1.0000
5.000 0.9027 0.00731 0.00233 -0.0434 0.3481 1.0000
5.250 0.9294 0.00744 0.00244 -0.0432 0.3424 1.0000
5.500 0.9561 0.00758 0.00257 -0.0430 0.3357 1.0000
5.750 0.9827 0.00775 0.00271 -0.0428 0.3287 1.0000
6.000 1.0093 0.00790 0.00285 -0.0426 0.3208 1.0000
6.250 1.0357 0.00809 0.00302 -0.0425 0.3129 1.0000
6.500 1.0621 0.00828 0.00319 -0.0423 0.3039 1.0000
6.750 1.0884 0.00848 0.00337 -0.0421 0.2958 1.0000
7.000 1.1145 0.00871 0.00358 -0.0419 0.2865 1.0000
7.250 1.1407 0.00893 0.00378 -0.0418 0.2771 1.0000
7.500 1.1665 0.00918 0.00401 -0.0416 0.2674 1.0000
7.750 1.1919 0.00948 0.00427 -0.0414 0.2564 1.0000
8.000 1.2173 0.00978 0.00453 -0.0412 0.2444 1.0000
8.250 1.2424 0.01010 0.00482 -0.0410 0.2326 1.0000
8.500 1.2671 0.01045 0.00514 -0.0407 0.2201 1.0000
8.750 1.2911 0.01086 0.00550 -0.0404 0.2060 1.0000
9.000 1.3145 0.01133 0.00590 -0.0400 0.1905 1.0000
9.250 1.3375 0.01182 0.00634 -0.0396 0.1757 1.0000
9.500 1.3590 0.01242 0.00685 -0.0391 0.1583 1.0000
9.750 1.3800 0.01304 0.00739 -0.0385 0.1411 1.0000
10.000 1.4007 0.01364 0.00794 -0.0378 0.1273 1.0000
10.250 1.4204 0.01428 0.00853 -0.0371 0.1140 1.0000
10.500 1.4394 0.01494 0.00915 -0.0363 0.1023 1.0000
10.750 1.4569 0.01566 0.00982 -0.0353 0.0909 1.0000
11.000 1.4722 0.01645 0.01057 -0.0341 0.0794 1.0000
11.250 1.4863 0.01726 0.01135 -0.0328 0.0704 1.0000
11.750 1.5006 0.01909 0.01316 -0.0282 0.0556 1.0000
12.000 1.5019 0.02030 0.01439 -0.0259 0.0508 1.0000
12.250 1.5012 0.02205 0.01615 -0.0243 0.0452 1.0000
12.500 1.4994 0.02425 0.01836 -0.0233 0.0381 1.0000
12.750 1.4980 0.02666 0.02077 -0.0228 0.0324 1.0000
13.000 1.5034 0.02855 0.02272 -0.0225 0.0309 1.0000
13.250 1.5023 0.03111 0.02531 -0.0222 0.0272 1.0000
13.500 1.5073 0.03311 0.02738 -0.0220 0.0270 1.0000
13.750 1.5024 0.03612 0.03043 -0.0219 0.0230 1.0000
14.000 1.5028 0.03864 0.03300 -0.0218 0.0215 1.0000
14.500 1.4960 0.04456 0.03901 -0.0218 0.0174 1.0000
14.750 1.4935 0.04749 0.04201 -0.0219 0.0164 1.0000
15.000 1.4908 0.05049 0.04507 -0.0221 0.0152 1.0000
15.250 1.4865 0.05382 0.04845 -0.0226 0.0137 1.0000
15.500 1.4845 0.05700 0.05170 -0.0230 0.0130 1.0000
15.750 1.4829 0.06018 0.05494 -0.0236 0.0123 1.0000
16.000 1.4803 0.06356 0.05839 -0.0243 0.0114 1.0000
16.250 1.4776 0.06701 0.06190 -0.0250 0.0108 1.0000
16.500 1.4744 0.07063 0.06560 -0.0259 0.0099 1.0000
16.750 1.4708 0.07437 0.06940 -0.0269 0.0090 1.0000
17.000 1.4675 0.07812 0.07321 -0.0279 0.0085 1.0000
17.250 1.4635 0.08205 0.07721 -0.0291 0.0077 1.0000
17.500 1.4590 0.08614 0.08138 -0.0304 0.0071 1.0000
17.750 1.4556 0.09012 0.08542 -0.0317 0.0068 1.0000
18.000 1.4516 0.09426 0.08964 -0.0332 0.0065 1.0000
18.250 1.4468 0.09859 0.09405 -0.0348 0.0059 1.0000
18.500 1.4431 0.10282 0.09836 -0.0364 0.0056 1.0000
18.750 1.4371 0.10748 0.10309 -0.0383 0.0052 1.0000
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