EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 598 AIRFOIL (e598-il) Reynolds number: 500,000 Max Cl/Cd: 109.33 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e598-il-500000.txt Download as CSV file: xf-e598-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3213 0.08656 0.08334 -0.0133 0.6394 0.0213
-7.750 -0.3327 0.08082 0.07763 -0.0180 0.6351 0.0220
-7.500 -0.3440 0.07574 0.07257 -0.0223 0.6306 0.0221
-6.750 -0.3903 0.03155 0.02736 -0.0459 0.6252 0.0124
-6.500 -0.3775 0.02643 0.02171 -0.0462 0.6198 0.0119
-6.250 -0.3614 0.02169 0.01616 -0.0457 0.6148 0.0112
-6.000 -0.3392 0.01900 0.01291 -0.0450 0.6089 0.0109
-5.750 -0.3143 0.01751 0.01110 -0.0445 0.6031 0.0109
-5.500 -0.2886 0.01643 0.00977 -0.0440 0.5980 0.0110
-5.250 -0.2622 0.01548 0.00867 -0.0436 0.5924 0.0113
-5.000 -0.2356 0.01471 0.00774 -0.0432 0.5870 0.0116
-4.750 -0.2088 0.01407 0.00692 -0.0428 0.5821 0.0123
-4.500 -0.1819 0.01333 0.00611 -0.0424 0.5773 0.0130
-4.250 -0.1545 0.01281 0.00553 -0.0421 0.5725 0.0144
-4.000 -0.1272 0.01232 0.00494 -0.0418 0.5679 0.0166
-3.750 -0.0996 0.01187 0.00444 -0.0415 0.5635 0.0219
-3.500 -0.0720 0.01143 0.00404 -0.0413 0.5590 0.0329
-3.250 -0.0440 0.01123 0.00385 -0.0412 0.5547 0.0437
-3.000 -0.0161 0.01114 0.00373 -0.0410 0.5505 0.0534
-2.750 0.0122 0.01103 0.00363 -0.0410 0.5464 0.0630
-2.500 0.0404 0.01089 0.00351 -0.0409 0.5422 0.0727
-2.250 0.0685 0.01074 0.00335 -0.0407 0.5382 0.0822
-2.000 0.0965 0.01065 0.00319 -0.0406 0.5342 0.0915
-1.750 0.1248 0.01056 0.00310 -0.0405 0.5303 0.1012
-1.500 0.1529 0.01039 0.00297 -0.0404 0.5264 0.1131
-1.250 0.1810 0.01026 0.00285 -0.0403 0.5225 0.1259
-1.000 0.2090 0.01017 0.00274 -0.0402 0.5187 0.1400
-0.750 0.2371 0.01009 0.00267 -0.0401 0.5150 0.1568
-0.500 0.2653 0.00995 0.00261 -0.0400 0.5112 0.1785
-0.250 0.2933 0.00980 0.00255 -0.0399 0.5072 0.2116
0.000 0.3208 0.00962 0.00251 -0.0398 0.5035 0.2685
0.250 0.3471 0.00929 0.00251 -0.0397 0.4998 0.3905
0.500 0.3887 0.00770 0.00260 -0.0422 0.4958 0.9733
0.750 0.4431 0.00772 0.00251 -0.0477 0.4910 1.0000
1.000 0.4697 0.00780 0.00250 -0.0473 0.4873 1.0000
1.250 0.4962 0.00792 0.00252 -0.0469 0.4836 1.0000
1.500 0.5232 0.00796 0.00255 -0.0466 0.4797 1.0000
1.750 0.5500 0.00802 0.00256 -0.0463 0.4756 1.0000
2.000 0.5768 0.00810 0.00258 -0.0459 0.4718 1.0000
2.250 0.6034 0.00824 0.00264 -0.0456 0.4678 1.0000
2.500 0.6304 0.00829 0.00270 -0.0453 0.4639 1.0000
2.750 0.6574 0.00836 0.00274 -0.0450 0.4597 1.0000
3.000 0.6841 0.00845 0.00279 -0.0447 0.4556 1.0000
3.250 0.7108 0.00859 0.00287 -0.0444 0.4516 1.0000
3.500 0.7379 0.00865 0.00295 -0.0442 0.4472 1.0000
3.750 0.7648 0.00873 0.00302 -0.0439 0.4428 1.0000
4.000 0.7915 0.00885 0.00310 -0.0437 0.4386 1.0000
4.250 0.8184 0.00896 0.00321 -0.0434 0.4341 1.0000
4.500 0.8454 0.00904 0.00331 -0.0432 0.4292 1.0000
4.750 0.8722 0.00915 0.00340 -0.0430 0.4246 1.0000
5.000 0.8989 0.00930 0.00353 -0.0428 0.4199 1.0000
5.250 0.9259 0.00939 0.00366 -0.0426 0.4148 1.0000
5.500 0.9527 0.00950 0.00377 -0.0424 0.4096 1.0000
5.750 0.9793 0.00967 0.00392 -0.0422 0.4046 1.0000
6.000 1.0063 0.00976 0.00407 -0.0421 0.3988 1.0000
6.250 1.0328 0.00991 0.00421 -0.0419 0.3930 1.0000
6.500 1.0594 0.01006 0.00439 -0.0417 0.3870 1.0000
6.750 1.0859 0.01020 0.00454 -0.0416 0.3803 1.0000
7.000 1.1121 0.01039 0.00474 -0.0414 0.3739 1.0000
7.250 1.1386 0.01053 0.00493 -0.0412 0.3666 1.0000
7.500 1.1644 0.01076 0.00513 -0.0410 0.3597 1.0000
7.750 1.1907 0.01091 0.00536 -0.0409 0.3519 1.0000
8.000 1.2161 0.01116 0.00560 -0.0406 0.3444 1.0000
8.250 1.2420 0.01136 0.00585 -0.0405 0.3358 1.0000
8.500 1.2672 0.01162 0.00613 -0.0402 0.3272 1.0000
8.750 1.2921 0.01190 0.00642 -0.0399 0.3177 1.0000
9.000 1.3171 0.01216 0.00673 -0.0397 0.3081 1.0000
9.250 1.3412 0.01251 0.00708 -0.0394 0.2979 1.0000
9.500 1.3645 0.01290 0.00746 -0.0390 0.2863 1.0000
9.750 1.3881 0.01327 0.00786 -0.0386 0.2742 1.0000
10.000 1.4106 0.01370 0.00831 -0.0381 0.2611 1.0000
10.250 1.4319 0.01423 0.00882 -0.0376 0.2464 1.0000
10.500 1.4521 0.01481 0.00939 -0.0369 0.2314 1.0000
10.750 1.4708 0.01548 0.01004 -0.0361 0.2159 1.0000
11.000 1.4873 0.01627 0.01078 -0.0350 0.1996 1.0000
11.250 1.5021 0.01711 0.01159 -0.0338 0.1831 1.0000
11.500 1.5137 0.01808 0.01251 -0.0323 0.1661 1.0000
11.750 1.5207 0.01918 0.01358 -0.0302 0.1507 1.0000
12.000 1.5195 0.02044 0.01482 -0.0272 0.1390 1.0000
12.250 1.5159 0.02218 0.01657 -0.0251 0.1282 1.0000
12.500 1.5123 0.02440 0.01878 -0.0238 0.1184 1.0000
12.750 1.5116 0.02664 0.02105 -0.0232 0.1093 1.0000
13.000 1.5086 0.02926 0.02369 -0.0227 0.1007 1.0000
13.250 1.5034 0.03220 0.02664 -0.0224 0.0936 1.0000
13.500 1.4999 0.03503 0.02951 -0.0221 0.0864 1.0000
13.750 1.4945 0.03811 0.03262 -0.0220 0.0804 1.0000
14.000 1.4881 0.04135 0.03589 -0.0220 0.0745 1.0000
14.250 1.4826 0.04454 0.03913 -0.0220 0.0695 1.0000
14.500 1.4746 0.04806 0.04267 -0.0222 0.0645 1.0000
14.750 1.4680 0.05148 0.04615 -0.0224 0.0603 1.0000
15.000 1.4610 0.05513 0.04984 -0.0229 0.0560 1.0000
15.250 1.4545 0.05886 0.05361 -0.0235 0.0522 1.0000
15.500 1.4484 0.06266 0.05746 -0.0243 0.0484 1.0000
15.750 1.4405 0.06679 0.06163 -0.0252 0.0451 1.0000
16.000 1.4362 0.07055 0.06546 -0.0261 0.0420 1.0000
16.250 1.4269 0.07509 0.07004 -0.0273 0.0395 1.0000
16.500 1.4240 0.07881 0.07384 -0.0284 0.0366 1.0000
16.750 1.4168 0.08324 0.07831 -0.0297 0.0341 1.0000
17.000 1.4093 0.08783 0.08298 -0.0312 0.0323 1.0000
17.250 1.4057 0.09186 0.08708 -0.0326 0.0299 1.0000
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Polar data table (+)
Polar graphs
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