EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 639 AIRFOIL (e639-il) Reynolds number: 500,000 Max Cl/Cd: 100.53 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e639-il-500000.txt Download as CSV file: xf-e639-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 639 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2723 0.10330 0.10120 -0.0265 1.0000 0.0157
-9.500 -0.2694 0.10010 0.09803 -0.0276 1.0000 0.0160
-9.250 -0.2740 0.09605 0.09402 -0.0314 1.0000 0.0166
-9.000 -0.2441 0.08940 0.08734 -0.0426 0.9368 0.0167
-8.750 -0.1880 0.07953 0.07715 -0.0620 0.8610 0.0170
-8.500 -0.1823 0.07737 0.07466 -0.0615 0.7937 0.0172
-8.250 -0.1801 0.07513 0.07227 -0.0613 0.7591 0.0174
-8.000 -0.1819 0.07230 0.06935 -0.0622 0.7339 0.0175
-7.750 -0.1822 0.07011 0.06708 -0.0625 0.7130 0.0180
-7.500 -0.1898 0.06703 0.06393 -0.0633 0.6964 0.0180
-7.250 -0.1878 0.06412 0.06093 -0.0644 0.6808 0.0182
-6.750 -0.1794 0.05767 0.05429 -0.0663 0.6543 0.0192
-6.500 -0.1721 0.05415 0.05063 -0.0670 0.6428 0.0199
-6.250 -0.1497 0.03575 0.03207 -0.0631 0.6156 0.0212
-6.000 -0.1550 0.04422 0.04010 -0.0670 0.6245 0.0214
-5.750 -0.1434 0.04178 0.03759 -0.0664 0.6137 0.0217
-5.500 -0.1289 0.03994 0.03563 -0.0657 0.6033 0.0221
-5.250 -0.1127 0.03811 0.03369 -0.0650 0.5928 0.0228
-5.000 -0.0954 0.03598 0.03138 -0.0641 0.5833 0.0238
-4.750 -0.0718 0.03392 0.02878 -0.0618 0.5749 0.0266
-4.500 -0.0606 0.02970 0.02438 -0.0605 0.5668 0.0274
-4.250 -0.0410 0.02839 0.02298 -0.0599 0.5578 0.0282
-4.000 -0.0198 0.02718 0.02165 -0.0591 0.5487 0.0295
-3.750 0.0075 0.02740 0.02141 -0.0573 0.5407 0.0334
-3.500 0.0230 0.02350 0.01736 -0.0562 0.5337 0.0350
-3.250 0.0457 0.02247 0.01622 -0.0556 0.5262 0.0365
-3.000 0.0707 0.02174 0.01530 -0.0547 0.5185 0.0400
-2.750 0.0928 0.02011 0.01338 -0.0536 0.5118 0.0443
-2.500 0.1176 0.01926 0.01247 -0.0531 0.5045 0.0470
-2.250 0.1423 0.01868 0.01154 -0.0520 0.4983 0.0543
-2.000 0.1710 0.01546 0.00793 -0.0504 0.4930 0.0356
-1.750 0.1986 0.01405 0.00634 -0.0495 0.4870 0.0298
-1.500 0.2247 0.01312 0.00521 -0.0487 0.4815 0.0281
-1.250 0.2505 0.01257 0.00462 -0.0480 0.4757 0.0280
-1.000 0.2754 0.01216 0.00416 -0.0473 0.4701 0.0286
-0.750 0.3005 0.01187 0.00382 -0.0466 0.4651 0.0293
-0.500 0.3261 0.01161 0.00355 -0.0460 0.4601 0.0305
-0.250 0.3517 0.01145 0.00333 -0.0455 0.4553 0.0321
0.000 0.3773 0.01133 0.00315 -0.0449 0.4507 0.0332
0.250 0.4031 0.01111 0.00291 -0.0444 0.4461 0.0355
0.500 0.4293 0.01103 0.00279 -0.0439 0.4415 0.0402
0.750 0.4536 0.01079 0.00274 -0.0432 0.4375 0.1191
1.000 0.5187 0.00899 0.00332 -0.0505 0.4323 0.9754
1.250 0.6145 0.00930 0.00344 -0.0646 0.4257 0.9943
1.500 0.6694 0.00934 0.00334 -0.0705 0.4208 1.0000
1.750 0.6927 0.00937 0.00335 -0.0697 0.4173 1.0000
2.000 0.7158 0.00942 0.00338 -0.0689 0.4139 1.0000
2.250 0.7388 0.00950 0.00340 -0.0680 0.4105 1.0000
2.500 0.7615 0.00965 0.00346 -0.0671 0.4069 1.0000
2.750 0.7848 0.00970 0.00352 -0.0663 0.4038 1.0000
3.000 0.8080 0.00977 0.00358 -0.0655 0.4006 1.0000
3.250 0.8310 0.00985 0.00365 -0.0646 0.3975 1.0000
3.500 0.8538 0.00998 0.00372 -0.0637 0.3944 1.0000
3.750 0.8765 0.01016 0.00386 -0.0628 0.3912 1.0000
4.000 0.8994 0.01023 0.00396 -0.0619 0.3882 1.0000
4.250 0.9223 0.01034 0.00407 -0.0610 0.3852 1.0000
4.500 0.9451 0.01045 0.00418 -0.0601 0.3823 1.0000
4.750 0.9677 0.01061 0.00432 -0.0592 0.3794 1.0000
5.000 0.9902 0.01082 0.00449 -0.0583 0.3761 1.0000
5.250 1.0129 0.01092 0.00464 -0.0574 0.3734 1.0000
5.500 1.0356 0.01105 0.00480 -0.0565 0.3705 1.0000
5.750 1.0582 0.01119 0.00495 -0.0556 0.3676 1.0000
6.000 1.0806 0.01137 0.00511 -0.0547 0.3646 1.0000
6.250 1.1031 0.01162 0.00534 -0.0538 0.3615 1.0000
6.500 1.1255 0.01173 0.00553 -0.0529 0.3587 1.0000
6.750 1.1478 0.01186 0.00571 -0.0520 0.3554 1.0000
7.000 1.1700 0.01201 0.00587 -0.0510 0.3521 1.0000
7.250 1.1921 0.01223 0.00607 -0.0501 0.3487 1.0000
7.500 1.2141 0.01242 0.00632 -0.0492 0.3454 1.0000
7.750 1.2359 0.01254 0.00651 -0.0482 0.3417 1.0000
8.000 1.2576 0.01268 0.00668 -0.0472 0.3378 1.0000
8.250 1.2790 0.01291 0.00690 -0.0462 0.3340 1.0000
8.500 1.3005 0.01309 0.00715 -0.0452 0.3303 1.0000
8.750 1.3219 0.01323 0.00737 -0.0442 0.3263 1.0000
9.000 1.3430 0.01340 0.00758 -0.0431 0.3223 1.0000
9.250 1.3635 0.01370 0.00786 -0.0421 0.3181 1.0000
9.500 1.3843 0.01381 0.00810 -0.0410 0.3137 1.0000
9.750 1.4044 0.01397 0.00831 -0.0398 0.3084 1.0000
10.000 1.4234 0.01425 0.00859 -0.0385 0.3035 1.0000
10.250 1.4440 0.01440 0.00888 -0.0374 0.2985 1.0000
10.500 1.4628 0.01463 0.00915 -0.0361 0.2927 1.0000
10.750 1.4811 0.01489 0.00946 -0.0347 0.2864 1.0000
11.000 1.4973 0.01516 0.00975 -0.0330 0.2771 1.0000
11.250 1.5139 0.01545 0.01011 -0.0315 0.2670 1.0000
11.500 1.5262 0.01583 0.01051 -0.0291 0.2565 1.0000
11.750 1.5352 0.01631 0.01098 -0.0263 0.2460 1.0000
12.000 1.5428 0.01690 0.01157 -0.0235 0.2340 1.0000
12.250 1.5491 0.01763 0.01228 -0.0206 0.2203 1.0000
12.500 1.5537 0.01850 0.01316 -0.0179 0.2068 1.0000
12.750 1.5542 0.01967 0.01430 -0.0149 0.1911 1.0000
13.000 1.5528 0.02110 0.01572 -0.0123 0.1773 1.0000
13.250 1.5473 0.02302 0.01760 -0.0099 0.1624 1.0000
13.500 1.5409 0.02528 0.01986 -0.0081 0.1501 1.0000
13.750 1.5325 0.02802 0.02260 -0.0068 0.1385 1.0000
14.000 1.5226 0.03113 0.02573 -0.0060 0.1281 1.0000
14.250 1.5126 0.03448 0.02910 -0.0055 0.1182 1.0000
14.500 1.4990 0.03833 0.03297 -0.0053 0.1089 1.0000
15.000 1.4753 0.04600 0.04075 -0.0053 0.0965 1.0000
15.250 1.4592 0.05042 0.04521 -0.0056 0.0909 1.0000
15.500 1.4460 0.05465 0.04949 -0.0060 0.0844 1.0000
15.750 1.4288 0.05951 0.05438 -0.0067 0.0787 1.0000
16.000 1.4196 0.06352 0.05846 -0.0073 0.0742 1.0000
16.250 1.4056 0.06823 0.06322 -0.0082 0.0693 1.0000
16.500 1.3935 0.07277 0.06780 -0.0092 0.0637 1.0000
16.750 1.3802 0.07758 0.07264 -0.0103 0.0589 1.0000
17.000 1.3693 0.08218 0.07728 -0.0114 0.0537 1.0000
17.250 1.3562 0.08712 0.08225 -0.0128 0.0488 1.0000
17.500 1.3466 0.09168 0.08685 -0.0140 0.0440 1.0000
17.750 1.3352 0.09658 0.09177 -0.0155 0.0392 1.0000
18.000 1.3231 0.10167 0.09686 -0.0171 0.0328 1.0000
18.250 1.3124 0.10662 0.10184 -0.0188 0.0279 1.0000
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