EPPLER 642 AIRFOIL (e642-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 642 AIRFOIL (e642-il) Reynolds number: 100,000 Max Cl/Cd: 42.96 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e642-il-100000-n5.txt Download as CSV file: xf-e642-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 642 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3419 0.13772 0.13274 -0.0464 1.0000 0.0574
-12.750 -0.3481 0.13421 0.12931 -0.0499 1.0000 0.0580
-12.500 -0.3493 0.13044 0.12558 -0.0523 1.0000 0.0582
-12.250 -0.3493 0.12648 0.12169 -0.0544 1.0000 0.0582
-11.750 -0.3364 0.11402 0.10925 -0.0555 1.0000 0.0375
-11.250 -0.3336 0.10058 0.09586 -0.0641 0.9521 0.0305
-11.000 -0.3192 0.09619 0.09142 -0.0682 0.9248 0.0300
-10.750 -0.3090 0.09093 0.08609 -0.0733 0.9059 0.0294
-10.500 -0.3040 0.08518 0.08028 -0.0783 0.8899 0.0288
-10.250 -0.3068 0.07834 0.07337 -0.0841 0.8757 0.0281
-10.000 -0.3216 0.07004 0.06495 -0.0910 0.8630 0.0274
-9.500 -0.3695 0.05870 0.05319 -0.0943 0.8410 0.0262
-9.250 -0.3945 0.05451 0.04869 -0.0919 0.8322 0.0257
-9.000 -0.4206 0.05040 0.04413 -0.0879 0.8243 0.0251
-8.750 -0.4309 0.04708 0.04033 -0.0847 0.8184 0.0247
-8.250 -0.4264 0.04187 0.03437 -0.0800 0.8080 0.0247
-8.000 -0.4176 0.03940 0.03152 -0.0781 0.8044 0.0247
-7.750 -0.4058 0.03727 0.02914 -0.0766 0.7999 0.0250
-7.500 -0.3903 0.03572 0.02743 -0.0756 0.7958 0.0257
-7.250 -0.3729 0.03442 0.02594 -0.0746 0.7920 0.0268
-7.000 -0.3545 0.03276 0.02393 -0.0734 0.7889 0.0276
-6.750 -0.3348 0.03106 0.02193 -0.0723 0.7851 0.0283
-6.500 -0.3123 0.02946 0.02003 -0.0716 0.7817 0.0286
-6.250 -0.2877 0.02800 0.01830 -0.0711 0.7787 0.0291
-6.000 -0.2618 0.02671 0.01680 -0.0708 0.7761 0.0297
-5.750 -0.2357 0.02561 0.01549 -0.0705 0.7737 0.0305
-5.500 -0.2126 0.02462 0.01448 -0.0699 0.7705 0.0314
-5.250 -0.1909 0.02389 0.01374 -0.0691 0.7671 0.0328
-5.000 -0.1689 0.02331 0.01310 -0.0684 0.7640 0.0355
-4.750 -0.1471 0.02275 0.01243 -0.0674 0.7615 0.0382
-4.500 -0.1261 0.02214 0.01179 -0.0664 0.7591 0.0417
-4.250 -0.1044 0.02164 0.01117 -0.0654 0.7566 0.0464
-4.000 -0.0850 0.02115 0.01072 -0.0641 0.7531 0.0555
-3.750 -0.0654 0.02054 0.01033 -0.0629 0.7500 0.0890
-3.500 -0.0460 0.01978 0.01006 -0.0619 0.7473 0.1842
-3.250 -0.0366 0.01843 0.00991 -0.0592 0.7446 0.4238
-3.000 0.0152 0.01951 0.01231 -0.0586 0.7433 0.7785
-2.750 0.0182 0.01989 0.01255 -0.0537 0.7404 0.8131
-2.500 0.0453 0.02059 0.01310 -0.0527 0.7371 0.8354
-2.250 0.0724 0.02115 0.01351 -0.0517 0.7340 0.8561
-2.000 0.1174 0.02171 0.01387 -0.0539 0.7317 0.8767
-1.750 0.1678 0.02197 0.01393 -0.0576 0.7296 0.8912
-1.500 0.2106 0.02201 0.01379 -0.0604 0.7275 0.9006
-1.250 0.2470 0.02202 0.01365 -0.0622 0.7252 0.9077
-1.000 0.2740 0.02218 0.01374 -0.0625 0.7213 0.9154
-0.750 0.3038 0.02223 0.01370 -0.0634 0.7179 0.9213
-0.500 0.3367 0.02220 0.01359 -0.0647 0.7149 0.9261
-0.250 0.3579 0.02225 0.01354 -0.0637 0.7122 0.9326
0.000 0.3949 0.02212 0.01331 -0.0658 0.7101 0.9355
0.250 0.4203 0.02234 0.01354 -0.0662 0.7054 0.9401
0.500 0.4405 0.02249 0.01366 -0.0652 0.7014 0.9452
0.750 0.4699 0.02247 0.01360 -0.0660 0.6983 0.9483
1.000 0.5019 0.02239 0.01346 -0.0671 0.6957 0.9509
1.250 0.5263 0.02256 0.01362 -0.0671 0.6917 0.9544
1.500 0.5440 0.02283 0.01393 -0.0658 0.6866 0.9583
1.750 0.5698 0.02285 0.01394 -0.0658 0.6829 0.9609
2.000 0.6007 0.02276 0.01381 -0.0667 0.6800 0.9627
2.250 0.6239 0.02298 0.01409 -0.0665 0.6752 0.9654
2.500 0.6446 0.02321 0.01436 -0.0658 0.6697 0.9682
2.750 0.6694 0.02319 0.01434 -0.0655 0.6660 0.9704
3.000 0.6959 0.02307 0.01420 -0.0653 0.6632 0.9722
3.250 0.7121 0.02356 0.01482 -0.0642 0.6554 0.9746
3.500 0.7397 0.02350 0.01479 -0.0644 0.6510 0.9763
3.750 0.7701 0.02327 0.01456 -0.0649 0.6478 0.9775
4.000 0.7816 0.02380 0.01523 -0.0629 0.6394 0.9802
4.250 0.8076 0.02367 0.01513 -0.0626 0.6348 0.9819
4.500 0.8280 0.02372 0.01524 -0.0615 0.6290 0.9837
4.750 0.8466 0.02390 0.01553 -0.0604 0.6215 0.9853
5.000 0.8784 0.02352 0.01520 -0.0610 0.6174 0.9863
5.250 0.8918 0.02397 0.01579 -0.0592 0.6078 0.9890
5.500 0.9206 0.02358 0.01545 -0.0592 0.6027 0.9899
5.750 0.9304 0.02400 0.01600 -0.0567 0.5927 0.9924
6.000 0.9605 0.02350 0.01557 -0.0568 0.5870 0.9934
6.250 0.9726 0.02388 0.01610 -0.0549 0.5757 0.9964
6.500 0.9883 0.02402 0.01636 -0.0532 0.5656 0.9988
6.750 1.0146 0.02362 0.01606 -0.0527 0.5577 1.0000
7.000 1.0042 0.02416 0.01669 -0.0465 0.5460 1.0000
7.250 0.9951 0.02453 0.01713 -0.0404 0.5351 1.0000
7.500 0.9908 0.02456 0.01719 -0.0348 0.5253 1.0000
7.750 0.9898 0.02450 0.01717 -0.0298 0.5150 1.0000
8.000 0.9709 0.02498 0.01766 -0.0224 0.5032 1.0000
8.250 0.9664 0.02523 0.01793 -0.0174 0.4912 1.0000
8.500 0.9725 0.02529 0.01801 -0.0141 0.4782 1.0000
8.750 0.9832 0.02540 0.01815 -0.0115 0.4636 1.0000
9.000 0.9959 0.02561 0.01837 -0.0095 0.4472 1.0000
9.250 1.0098 0.02591 0.01867 -0.0078 0.4295 1.0000
9.500 1.0247 0.02626 0.01899 -0.0063 0.4104 1.0000
9.750 1.0347 0.02702 0.01974 -0.0047 0.3906 1.0000
10.000 1.0446 0.02786 0.02057 -0.0032 0.3696 1.0000
10.250 1.0545 0.02875 0.02140 -0.0017 0.3489 1.0000
10.500 1.0615 0.02994 0.02257 -0.0003 0.3279 1.0000
10.750 1.0680 0.03119 0.02376 0.0012 0.3068 1.0000
11.000 1.0736 0.03259 0.02511 0.0025 0.2865 1.0000
11.250 1.0786 0.03409 0.02658 0.0037 0.2670 1.0000
11.500 1.0828 0.03569 0.02816 0.0049 0.2481 1.0000
11.750 1.0872 0.03735 0.02978 0.0059 0.2310 1.0000
12.000 1.0906 0.03913 0.03156 0.0069 0.2136 1.0000
12.250 1.0938 0.04101 0.03343 0.0078 0.1968 1.0000
12.500 1.0946 0.04313 0.03552 0.0086 0.1787 1.0000
12.750 1.0949 0.04539 0.03773 0.0093 0.1616 1.0000
13.000 1.0938 0.04787 0.04015 0.0098 0.1444 1.0000
13.250 1.0938 0.05037 0.04265 0.0102 0.1262 1.0000
13.500 1.0928 0.05307 0.04529 0.0104 0.1093 1.0000
13.750 1.0914 0.05590 0.04809 0.0106 0.0943 1.0000
14.000 1.0903 0.05882 0.05099 0.0106 0.0812 1.0000
14.250 1.0894 0.06181 0.05400 0.0105 0.0700 1.0000
14.500 1.0875 0.06503 0.05724 0.0102 0.0598 1.0000
14.750 1.0851 0.06839 0.06065 0.0099 0.0520 1.0000
15.000 1.0800 0.07222 0.06452 0.0093 0.0448 1.0000
15.250 1.0748 0.07620 0.06855 0.0085 0.0402 1.0000
15.500 1.0694 0.08034 0.07279 0.0076 0.0362 1.0000
15.750 1.0630 0.08471 0.07726 0.0065 0.0331 1.0000
16.250 1.0523 0.09352 0.08630 0.0039 0.0292 1.0000
16.500 1.0482 0.09785 0.09076 0.0024 0.0276 1.0000
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