EPPLER 598 AIRFOIL (e598-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 598 AIRFOIL (e598-il) Reynolds number: 500,000 Max Cl/Cd: 106.3 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e598-il-500000-n5.txt Download as CSV file: xf-e598-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3599 0.09381 0.09031 -0.0076 0.6011 0.0070
-8.750 -0.3590 0.08968 0.08618 -0.0096 0.5967 0.0068
-8.250 -0.5565 0.02880 0.02427 -0.0454 0.6100 0.0053
-8.000 -0.5398 0.02544 0.02044 -0.0456 0.6038 0.0053
-7.750 -0.5194 0.02325 0.01788 -0.0455 0.5980 0.0054
-7.500 -0.4972 0.02150 0.01582 -0.0452 0.5919 0.0054
-7.250 -0.4738 0.02009 0.01413 -0.0448 0.5855 0.0055
-7.000 -0.4494 0.01892 0.01272 -0.0445 0.5799 0.0055
-6.750 -0.4243 0.01792 0.01151 -0.0441 0.5742 0.0056
-6.500 -0.3986 0.01706 0.01046 -0.0438 0.5689 0.0056
-6.250 -0.3729 0.01621 0.00942 -0.0434 0.5641 0.0058
-6.000 -0.3468 0.01542 0.00849 -0.0431 0.5589 0.0059
-5.750 -0.3202 0.01479 0.00773 -0.0429 0.5537 0.0061
-5.500 -0.2933 0.01428 0.00709 -0.0426 0.5493 0.0064
-5.250 -0.2660 0.01378 0.00650 -0.0424 0.5451 0.0067
-5.000 -0.2386 0.01335 0.00596 -0.0421 0.5404 0.0071
-4.750 -0.2111 0.01297 0.00545 -0.0419 0.5359 0.0077
-4.500 -0.1836 0.01255 0.00496 -0.0416 0.5319 0.0085
-4.250 -0.1558 0.01221 0.00454 -0.0414 0.5281 0.0097
-4.000 -0.1281 0.01187 0.00416 -0.0412 0.5239 0.0117
-3.750 -0.1004 0.01158 0.00382 -0.0410 0.5198 0.0153
-3.500 -0.0726 0.01132 0.00354 -0.0409 0.5161 0.0210
-3.250 -0.0447 0.01107 0.00332 -0.0407 0.5125 0.0291
-3.000 -0.0168 0.01086 0.00313 -0.0406 0.5087 0.0382
-2.750 0.0112 0.01071 0.00297 -0.0405 0.5047 0.0476
-2.500 0.0393 0.01059 0.00283 -0.0404 0.5011 0.0565
-2.250 0.0674 0.01044 0.00270 -0.0403 0.4979 0.0647
-2.000 0.0957 0.01031 0.00257 -0.0402 0.4942 0.0725
-1.750 0.1239 0.01021 0.00246 -0.0401 0.4904 0.0806
-1.500 0.1521 0.01013 0.00236 -0.0400 0.4867 0.0894
-1.250 0.1803 0.01005 0.00227 -0.0399 0.4836 0.0997
-1.000 0.2086 0.00996 0.00220 -0.0398 0.4801 0.1101
-0.750 0.2369 0.00988 0.00213 -0.0398 0.4762 0.1211
-0.500 0.2652 0.00982 0.00207 -0.0397 0.4726 0.1333
-0.250 0.2933 0.00978 0.00202 -0.0396 0.4692 0.1482
0.000 0.3215 0.00970 0.00199 -0.0396 0.4658 0.1669
0.250 0.3497 0.00961 0.00197 -0.0396 0.4620 0.1913
0.500 0.3777 0.00952 0.00196 -0.0395 0.4583 0.2248
0.750 0.4056 0.00942 0.00196 -0.0395 0.4546 0.2695
1.000 0.4330 0.00925 0.00197 -0.0394 0.4511 0.3414
1.500 0.5184 0.00764 0.00207 -0.0455 0.4425 0.9977
1.750 0.5491 0.00772 0.00207 -0.0460 0.4385 1.0000
2.000 0.5759 0.00780 0.00211 -0.0457 0.4349 1.0000
2.250 0.6028 0.00787 0.00215 -0.0454 0.4306 1.0000
2.500 0.6297 0.00795 0.00219 -0.0451 0.4263 1.0000
2.750 0.6564 0.00806 0.00224 -0.0448 0.4223 1.0000
3.000 0.6833 0.00814 0.00231 -0.0445 0.4182 1.0000
3.250 0.7102 0.00823 0.00238 -0.0443 0.4136 1.0000
3.500 0.7370 0.00834 0.00245 -0.0440 0.4090 1.0000
3.750 0.7637 0.00845 0.00254 -0.0437 0.4047 1.0000
4.000 0.7907 0.00855 0.00264 -0.0435 0.4000 1.0000
4.250 0.8174 0.00867 0.00274 -0.0433 0.3949 1.0000
4.500 0.8441 0.00881 0.00284 -0.0430 0.3901 1.0000
4.750 0.8710 0.00892 0.00297 -0.0429 0.3850 1.0000
5.000 0.8978 0.00905 0.00310 -0.0426 0.3795 1.0000
5.250 0.9243 0.00921 0.00324 -0.0424 0.3745 1.0000
5.500 0.9512 0.00934 0.00339 -0.0423 0.3688 1.0000
5.750 0.9777 0.00951 0.00355 -0.0421 0.3627 1.0000
6.000 1.0043 0.00967 0.00371 -0.0419 0.3569 1.0000
6.250 1.0308 0.00984 0.00389 -0.0417 0.3500 1.0000
6.500 1.0570 0.01004 0.00409 -0.0415 0.3432 1.0000
6.750 1.0833 0.01023 0.00429 -0.0414 0.3352 1.0000
7.000 1.1092 0.01045 0.00451 -0.0412 0.3275 1.0000
7.250 1.1351 0.01068 0.00475 -0.0410 0.3187 1.0000
7.500 1.1608 0.01092 0.00499 -0.0408 0.3105 1.0000
7.750 1.1860 0.01122 0.00528 -0.0405 0.3012 1.0000
8.000 1.2114 0.01148 0.00556 -0.0403 0.2917 1.0000
8.250 1.2362 0.01180 0.00587 -0.0400 0.2816 1.0000
8.500 1.2604 0.01217 0.00623 -0.0397 0.2705 1.0000
8.750 1.2845 0.01254 0.00660 -0.0394 0.2584 1.0000
9.000 1.3081 0.01294 0.00700 -0.0390 0.2464 1.0000
9.250 1.3308 0.01340 0.00745 -0.0386 0.2332 1.0000
9.500 1.3527 0.01393 0.00795 -0.0381 0.2186 1.0000
9.750 1.3735 0.01452 0.00850 -0.0375 0.2036 1.0000
10.000 1.3931 0.01518 0.00912 -0.0367 0.1879 1.0000
10.250 1.4106 0.01597 0.00984 -0.0358 0.1710 1.0000
10.500 1.4271 0.01677 0.01059 -0.0348 0.1546 1.0000
10.750 1.4418 0.01762 0.01141 -0.0336 0.1401 1.0000
11.000 1.4541 0.01855 0.01232 -0.0321 0.1270 1.0000
11.250 1.4628 0.01957 0.01332 -0.0303 0.1157 1.0000
11.500 1.4639 0.02073 0.01448 -0.0275 0.1067 1.0000
11.750 1.4647 0.02220 0.01597 -0.0256 0.0984 1.0000
12.000 1.4650 0.02406 0.01786 -0.0244 0.0911 1.0000
12.250 1.4638 0.02633 0.02014 -0.0237 0.0831 1.0000
12.500 1.4654 0.02851 0.02237 -0.0232 0.0767 1.0000
12.750 1.4645 0.03102 0.02491 -0.0229 0.0713 1.0000
13.000 1.4636 0.03358 0.02751 -0.0227 0.0655 1.0000
13.250 1.4616 0.03632 0.03029 -0.0225 0.0611 1.0000
13.500 1.4587 0.03917 0.03318 -0.0224 0.0562 1.0000
13.750 1.4556 0.04208 0.03613 -0.0224 0.0528 1.0000
14.000 1.4526 0.04503 0.03915 -0.0225 0.0490 1.0000
14.500 1.4442 0.05133 0.04556 -0.0228 0.0426 1.0000
14.750 1.4399 0.05466 0.04894 -0.0232 0.0399 1.0000
15.000 1.4364 0.05801 0.05235 -0.0238 0.0374 1.0000
15.250 1.4325 0.06152 0.05592 -0.0244 0.0346 1.0000
15.500 1.4281 0.06518 0.05963 -0.0252 0.0323 1.0000
15.750 1.4249 0.06874 0.06326 -0.0260 0.0299 1.0000
16.000 1.4196 0.07268 0.06725 -0.0270 0.0278 1.0000
16.250 1.4170 0.07635 0.07100 -0.0280 0.0261 1.0000
16.500 1.4115 0.08049 0.07519 -0.0292 0.0240 1.0000
16.750 1.4076 0.08446 0.07923 -0.0304 0.0222 1.0000
17.000 1.4039 0.08852 0.08337 -0.0317 0.0209 1.0000
17.250 1.3978 0.09294 0.08785 -0.0332 0.0192 1.0000
17.500 1.3943 0.09706 0.09205 -0.0347 0.0179 1.0000
17.750 1.3897 0.10145 0.09652 -0.0363 0.0169 1.0000
18.000 1.3844 0.10601 0.10116 -0.0381 0.0163 1.0000
18.250 1.3801 0.11040 0.10562 -0.0399 0.0146 1.0000
18.500 1.3752 0.11501 0.11031 -0.0418 0.0138 1.0000
18.750 1.3699 0.11975 0.11513 -0.0439 0.0130 1.0000
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Polar data table (+)
Polar graphs
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