EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 639 AIRFOIL (e639-il) Reynolds number: 200,000 Max Cl/Cd: 69.25 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e639-il-200000-n5.txt Download as CSV file: xf-e639-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2831 0.11465 0.11122 -0.0260 1.0000 0.0215
-10.250 -0.2875 0.11133 0.10795 -0.0296 1.0000 0.0219
-10.000 -0.2856 0.10805 0.10472 -0.0314 1.0000 0.0219
-9.750 -0.2765 0.10436 0.10108 -0.0298 1.0000 0.0224
-9.500 -0.2703 0.10144 0.09819 -0.0298 1.0000 0.0227
-9.250 -0.2420 0.09679 0.09350 -0.0361 0.9138 0.0237
-9.000 -0.1996 0.09032 0.08672 -0.0486 0.8409 0.0252
-8.750 -0.1874 0.08647 0.08267 -0.0528 0.7942 0.0261
-8.500 -0.1868 0.08303 0.07912 -0.0558 0.7647 0.0271
-8.250 -0.1931 0.07938 0.07541 -0.0598 0.7420 0.0275
-8.000 -0.1971 0.07604 0.07200 -0.0622 0.7226 0.0276
-7.750 -0.2043 0.07247 0.06832 -0.0645 0.7071 0.0278
-7.500 -0.2036 0.06894 0.06464 -0.0660 0.6929 0.0278
-7.250 -0.2014 0.06503 0.06065 -0.0663 0.6800 0.0281
-7.000 -0.1949 0.06208 0.05762 -0.0658 0.6668 0.0284
-6.750 -0.1865 0.05971 0.05519 -0.0651 0.6537 0.0289
-6.500 -0.1773 0.05727 0.05265 -0.0649 0.6416 0.0298
-6.250 -0.1676 0.05444 0.04968 -0.0650 0.6310 0.0304
-6.000 -0.1548 0.05159 0.04624 -0.0654 0.6226 0.0349
-5.500 -0.1317 0.04508 0.03964 -0.0645 0.6035 0.0363
-5.250 -0.1164 0.04282 0.03723 -0.0638 0.5939 0.0371
-5.000 -0.0999 0.04054 0.03476 -0.0630 0.5849 0.0381
-4.750 -0.0826 0.03814 0.03211 -0.0620 0.5765 0.0388
-4.250 -0.0488 0.02774 0.02034 -0.0565 0.5636 0.0224
-4.000 -0.0272 0.02667 0.01916 -0.0558 0.5553 0.0231
-3.750 -0.0048 0.02564 0.01793 -0.0551 0.5473 0.0244
-3.500 0.0181 0.02378 0.01571 -0.0538 0.5403 0.0242
-3.250 0.0420 0.02195 0.01348 -0.0526 0.5330 0.0237
-3.000 0.0670 0.02054 0.01173 -0.0516 0.5260 0.0236
-2.750 0.0927 0.01943 0.01034 -0.0508 0.5187 0.0236
-2.500 0.1186 0.01853 0.00923 -0.0502 0.5122 0.0239
-2.250 0.1448 0.01775 0.00830 -0.0496 0.5055 0.0243
-2.000 0.1706 0.01713 0.00753 -0.0490 0.4997 0.0250
-1.750 0.1966 0.01664 0.00696 -0.0485 0.4934 0.0265
-1.500 0.2223 0.01621 0.00641 -0.0479 0.4874 0.0274
-1.250 0.2473 0.01577 0.00589 -0.0472 0.4821 0.0278
-1.000 0.2717 0.01528 0.00538 -0.0464 0.4762 0.0284
-0.750 0.2961 0.01495 0.00500 -0.0457 0.4714 0.0294
-0.500 0.3210 0.01473 0.00472 -0.0450 0.4668 0.0307
-0.250 0.3464 0.01455 0.00449 -0.0444 0.4616 0.0324
0.000 0.3717 0.01443 0.00430 -0.0439 0.4568 0.0359
0.250 0.3971 0.01434 0.00415 -0.0433 0.4525 0.0418
0.500 0.4224 0.01418 0.00405 -0.0427 0.4477 0.0619
1.000 0.5962 0.01229 0.00441 -0.0665 0.4352 1.0000
1.250 0.6190 0.01237 0.00441 -0.0656 0.4308 1.0000
1.500 0.6416 0.01248 0.00442 -0.0647 0.4270 1.0000
1.750 0.6642 0.01261 0.00444 -0.0638 0.4239 1.0000
2.000 0.6871 0.01273 0.00452 -0.0629 0.4202 1.0000
2.250 0.7098 0.01284 0.00460 -0.0620 0.4163 1.0000
2.500 0.7324 0.01298 0.00468 -0.0610 0.4126 1.0000
2.750 0.7549 0.01314 0.00475 -0.0601 0.4095 1.0000
3.000 0.7777 0.01330 0.00488 -0.0592 0.4064 1.0000
3.250 0.8004 0.01345 0.00503 -0.0583 0.4030 1.0000
3.500 0.8230 0.01361 0.00517 -0.0574 0.3995 1.0000
3.750 0.8455 0.01378 0.00530 -0.0564 0.3963 1.0000
4.000 0.8680 0.01399 0.00544 -0.0555 0.3935 1.0000
4.250 0.8906 0.01416 0.00566 -0.0546 0.3902 1.0000
4.500 0.9131 0.01435 0.00587 -0.0537 0.3869 1.0000
4.750 0.9356 0.01454 0.00607 -0.0528 0.3837 1.0000
5.000 0.9580 0.01475 0.00626 -0.0519 0.3808 1.0000
5.250 0.9806 0.01498 0.00645 -0.0510 0.3780 1.0000
5.500 1.0028 0.01520 0.00674 -0.0501 0.3748 1.0000
5.750 1.0250 0.01542 0.00702 -0.0492 0.3716 1.0000
6.000 1.0472 0.01564 0.00726 -0.0483 0.3684 1.0000
6.250 1.0696 0.01587 0.00748 -0.0474 0.3656 1.0000
6.500 1.0919 0.01614 0.00776 -0.0466 0.3629 1.0000
6.750 1.1136 0.01639 0.00812 -0.0456 0.3596 1.0000
7.000 1.1353 0.01664 0.00844 -0.0447 0.3561 1.0000
7.250 1.1570 0.01688 0.00872 -0.0438 0.3529 1.0000
7.500 1.1791 0.01715 0.00900 -0.0429 0.3501 1.0000
7.750 1.2002 0.01744 0.00937 -0.0419 0.3467 1.0000
8.000 1.2209 0.01771 0.00975 -0.0409 0.3428 1.0000
8.250 1.2417 0.01797 0.01008 -0.0398 0.3390 1.0000
8.500 1.2630 0.01824 0.01037 -0.0389 0.3355 1.0000
8.750 1.2828 0.01854 0.01079 -0.0377 0.3313 1.0000
9.000 1.3023 0.01883 0.01119 -0.0365 0.3265 1.0000
9.250 1.3220 0.01909 0.01150 -0.0354 0.3222 1.0000
9.500 1.3410 0.01941 0.01191 -0.0342 0.3176 1.0000
9.750 1.3591 0.01973 0.01238 -0.0328 0.3124 1.0000
10.000 1.3772 0.02004 0.01274 -0.0315 0.3078 1.0000
10.250 1.3946 0.02040 0.01321 -0.0301 0.3029 1.0000
10.500 1.4105 0.02077 0.01372 -0.0285 0.2970 1.0000
10.750 1.4253 0.02112 0.01409 -0.0267 0.2915 1.0000
11.000 1.4385 0.02156 0.01471 -0.0247 0.2846 1.0000
11.250 1.4481 0.02199 0.01518 -0.0221 0.2784 1.0000
11.500 1.4569 0.02252 0.01584 -0.0196 0.2712 1.0000
11.750 1.4644 0.02312 0.01651 -0.0171 0.2646 1.0000
12.000 1.4723 0.02383 0.01735 -0.0148 0.2572 1.0000
12.250 1.4761 0.02473 0.01829 -0.0124 0.2493 1.0000
12.500 1.4801 0.02579 0.01947 -0.0103 0.2400 1.0000
12.750 1.4803 0.02718 0.02092 -0.0083 0.2297 1.0000
13.000 1.4767 0.02901 0.02278 -0.0065 0.2178 1.0000
13.250 1.4701 0.03132 0.02512 -0.0051 0.2053 1.0000
13.500 1.4613 0.03410 0.02791 -0.0042 0.1933 1.0000
13.750 1.4493 0.03742 0.03124 -0.0036 0.1811 1.0000
14.000 1.4354 0.04115 0.03498 -0.0034 0.1696 1.0000
14.250 1.4218 0.04503 0.03892 -0.0034 0.1592 1.0000
14.500 1.4079 0.04910 0.04303 -0.0036 0.1508 1.0000
14.750 1.3937 0.05331 0.04728 -0.0040 0.1437 1.0000
15.000 1.3773 0.05797 0.05197 -0.0047 0.1344 1.0000
15.250 1.3624 0.06261 0.05665 -0.0055 0.1271 1.0000
15.500 1.3482 0.06735 0.06142 -0.0065 0.1194 1.0000
15.750 1.3382 0.07163 0.06576 -0.0075 0.1140 1.0000
16.000 1.3251 0.07645 0.07062 -0.0087 0.1067 1.0000
16.250 1.3135 0.08119 0.07539 -0.0100 0.0994 1.0000
16.500 1.3018 0.08602 0.08025 -0.0114 0.0934 1.0000
16.750 1.2945 0.09031 0.08460 -0.0127 0.0878 1.0000
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Polar data table (+)
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