EPPLER 635 AIRFOIL (e635-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 635 AIRFOIL (e635-il) Reynolds number: 200,000 Max Cl/Cd: 63.99 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e635-il-200000-n5.txt Download as CSV file: xf-e635-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 635 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5092 0.08800 0.08492 -0.0060 1.0000 0.0228
-8.750 -0.5335 0.07515 0.07203 -0.0104 1.0000 0.0172
-8.500 -0.5368 0.07286 0.06976 -0.0092 1.0000 0.0169
-8.250 -0.5441 0.06981 0.06670 -0.0082 1.0000 0.0166
-8.000 -0.5440 0.06566 0.06245 -0.0092 0.9008 0.0163
-7.750 -0.5444 0.06160 0.05805 -0.0088 0.8229 0.0160
-7.500 -0.5464 0.05778 0.05395 -0.0071 0.7861 0.0157
-7.250 -0.5471 0.05373 0.04961 -0.0049 0.7596 0.0155
-7.000 -0.5447 0.04967 0.04523 -0.0027 0.7384 0.0153
-6.750 -0.5403 0.04548 0.04068 -0.0001 0.7200 0.0152
-6.500 -0.5336 0.04125 0.03604 0.0026 0.7034 0.0152
-6.250 -0.5250 0.03706 0.03138 0.0056 0.6885 0.0154
-6.000 -0.5141 0.03287 0.02657 0.0088 0.6743 0.0164
-5.750 -0.5002 0.02946 0.02244 0.0119 0.6606 0.0174
-5.500 -0.4818 0.02749 0.02019 0.0134 0.6458 0.0180
-5.250 -0.4608 0.02581 0.01819 0.0148 0.6316 0.0185
-5.000 -0.4382 0.02432 0.01639 0.0159 0.6180 0.0191
-4.750 -0.4142 0.02287 0.01461 0.0170 0.6052 0.0198
-4.500 -0.3890 0.02171 0.01315 0.0178 0.5927 0.0212
-4.250 -0.3632 0.02087 0.01196 0.0186 0.5806 0.0226
-4.000 -0.3363 0.01946 0.01036 0.0190 0.5687 0.0234
-3.750 -0.3100 0.01844 0.00924 0.0195 0.5576 0.0243
-3.500 -0.2841 0.01770 0.00841 0.0200 0.5471 0.0253
-3.250 -0.2585 0.01717 0.00777 0.0206 0.5366 0.0272
-3.000 -0.2331 0.01660 0.00711 0.0212 0.5264 0.0286
-2.750 -0.2084 0.01607 0.00645 0.0221 0.5173 0.0295
-2.500 -0.1847 0.01549 0.00580 0.0230 0.5084 0.0306
-2.250 -0.1608 0.01504 0.00530 0.0239 0.4998 0.0322
-2.000 -0.1362 0.01476 0.00493 0.0247 0.4914 0.0349
-1.750 -0.1111 0.01451 0.00459 0.0254 0.4830 0.0380
-1.500 -0.0867 0.01424 0.00425 0.0262 0.4758 0.0421
-1.250 -0.0617 0.01399 0.00398 0.0270 0.4681 0.0521
-1.000 -0.0388 0.01359 0.00374 0.0280 0.4613 0.1066
-0.750 -0.0305 0.01201 0.00344 0.0312 0.4554 0.4427
-0.500 0.0872 0.01211 0.00498 0.0154 0.4429 0.9341
-0.250 0.1612 0.01301 0.00566 0.0071 0.4330 0.9623
0.000 0.1956 0.01305 0.00557 0.0058 0.4264 0.9668
0.250 0.2228 0.01312 0.00552 0.0058 0.4202 0.9711
0.500 0.2557 0.01312 0.00538 0.0047 0.4147 0.9733
0.750 0.2883 0.01309 0.00529 0.0036 0.4084 0.9757
1.000 0.3193 0.01311 0.00521 0.0028 0.4028 0.9784
1.250 0.3487 0.01316 0.00517 0.0023 0.3974 0.9813
1.500 0.3777 0.01320 0.00517 0.0020 0.3921 0.9840
1.750 0.4097 0.01320 0.00507 0.0009 0.3871 0.9858
2.000 0.4412 0.01320 0.00504 0.0000 0.3817 0.9879
2.250 0.4717 0.01322 0.00503 -0.0007 0.3766 0.9901
2.500 0.5017 0.01328 0.00502 -0.0014 0.3723 0.9923
2.750 0.5317 0.01334 0.00506 -0.0020 0.3676 0.9943
3.000 0.5627 0.01334 0.00507 -0.0029 0.3623 0.9960
3.250 0.5934 0.01339 0.00507 -0.0037 0.3581 0.9978
3.500 0.6244 0.01345 0.00512 -0.0046 0.3540 0.9996
3.750 0.6500 0.01354 0.00525 -0.0043 0.3495 1.0000
4.000 0.6739 0.01365 0.00535 -0.0037 0.3452 1.0000
4.250 0.6977 0.01380 0.00546 -0.0031 0.3415 1.0000
4.500 0.7219 0.01392 0.00566 -0.0026 0.3373 1.0000
4.750 0.7458 0.01406 0.00584 -0.0020 0.3333 1.0000
5.000 0.7696 0.01421 0.00599 -0.0014 0.3295 1.0000
5.250 0.7933 0.01438 0.00616 -0.0008 0.3258 1.0000
5.500 0.8173 0.01453 0.00642 -0.0002 0.3214 1.0000
5.750 0.8409 0.01470 0.00664 0.0004 0.3173 1.0000
6.000 0.8644 0.01489 0.00683 0.0010 0.3136 1.0000
6.250 0.8879 0.01508 0.00711 0.0016 0.3092 1.0000
6.500 0.9113 0.01526 0.00738 0.0022 0.3042 1.0000
6.750 0.9344 0.01546 0.00759 0.0029 0.2996 1.0000
7.000 0.9574 0.01567 0.00789 0.0036 0.2947 1.0000
7.250 0.9803 0.01588 0.00821 0.0043 0.2891 1.0000
7.500 1.0027 0.01611 0.00845 0.0051 0.2843 1.0000
7.750 1.0253 0.01634 0.00882 0.0058 0.2784 1.0000
8.000 1.0474 0.01658 0.00913 0.0065 0.2725 1.0000
8.250 1.0693 0.01685 0.00947 0.0074 0.2669 1.0000
8.500 1.0910 0.01711 0.00986 0.0082 0.2599 1.0000
8.750 1.1121 0.01741 0.01022 0.0091 0.2536 1.0000
9.000 1.1332 0.01771 0.01065 0.0100 0.2460 1.0000
9.250 1.1534 0.01805 0.01106 0.0109 0.2384 1.0000
9.500 1.1731 0.01841 0.01152 0.0120 0.2293 1.0000
9.750 1.1924 0.01881 0.01203 0.0130 0.2200 1.0000
10.000 1.2105 0.01927 0.01256 0.0142 0.2097 1.0000
10.250 1.2272 0.01981 0.01316 0.0156 0.1983 1.0000
10.500 1.2424 0.02044 0.01383 0.0170 0.1850 1.0000
10.750 1.2558 0.02116 0.01462 0.0187 0.1709 1.0000
11.000 1.2666 0.02202 0.01550 0.0206 0.1564 1.0000
11.250 1.2742 0.02302 0.01652 0.0228 0.1428 1.0000
11.500 1.2776 0.02419 0.01769 0.0254 0.1307 1.0000
11.750 1.2756 0.02557 0.01907 0.0285 0.1198 1.0000
12.000 1.2658 0.02692 0.02047 0.0326 0.1113 1.0000
12.250 1.2538 0.02879 0.02239 0.0355 0.1065 1.0000
12.500 1.2437 0.03128 0.02493 0.0369 0.0988 1.0000
12.750 1.2328 0.03432 0.02803 0.0373 0.0926 1.0000
13.000 1.2222 0.03767 0.03142 0.0372 0.0859 1.0000
13.250 1.2100 0.04138 0.03518 0.0368 0.0805 1.0000
13.500 1.2005 0.04491 0.03880 0.0363 0.0761 1.0000
13.750 1.1866 0.04905 0.04298 0.0355 0.0719 1.0000
14.000 1.1763 0.05287 0.04687 0.0348 0.0681 1.0000
14.250 1.1633 0.05708 0.05114 0.0338 0.0633 1.0000
14.750 1.1391 0.06560 0.05979 0.0316 0.0559 1.0000
15.000 1.1286 0.06992 0.06417 0.0304 0.0526 1.0000
15.500 1.1087 0.07878 0.07313 0.0275 0.0460 1.0000
15.750 1.0992 0.08328 0.07769 0.0260 0.0426 1.0000
16.000 1.0893 0.08795 0.08242 0.0244 0.0405 1.0000
16.250 1.0824 0.09224 0.08678 0.0229 0.0385 1.0000
16.500 1.0734 0.09693 0.09152 0.0212 0.0343 1.0000
16.750 1.0656 0.10150 0.09617 0.0195 0.0328 1.0000
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Polar data table (+)
Polar graphs
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