EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 639 AIRFOIL (e639-il) Reynolds number: 100,000 Max Cl/Cd: 45.97 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e639-il-100000-n5.txt Download as CSV file: xf-e639-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2609 0.10000 0.09560 -0.0311 1.0000 0.0468
-8.750 -0.2580 0.09716 0.09283 -0.0317 1.0000 0.0478
-8.500 -0.2569 0.09435 0.09012 -0.0324 1.0000 0.0493
-8.250 -0.1411 0.07570 0.07137 -0.0507 0.8181 0.0571
-8.000 -0.1352 0.07239 0.06794 -0.0513 0.7918 0.0583
-7.750 -0.1331 0.06905 0.06452 -0.0521 0.7706 0.0598
-7.250 -0.1953 0.07307 0.06843 -0.0592 0.7937 0.0581
-7.000 -0.1885 0.07010 0.06532 -0.0603 0.7699 0.0594
-6.750 -0.1824 0.06706 0.06213 -0.0615 0.7500 0.0611
-6.500 -0.1757 0.06397 0.05889 -0.0627 0.7329 0.0631
-6.250 -0.1713 0.06245 0.05684 -0.0654 0.7183 0.0676
-6.000 -0.1629 0.06007 0.05411 -0.0651 0.7047 0.0681
-5.750 -0.1496 0.05471 0.04883 -0.0652 0.6918 0.0693
-5.500 -0.1351 0.05161 0.04564 -0.0647 0.6792 0.0703
-5.250 -0.1160 0.04605 0.03954 -0.0638 0.6698 0.0424
-5.000 -0.1005 0.04327 0.03657 -0.0631 0.6583 0.0413
-4.750 -0.0833 0.04069 0.03368 -0.0621 0.6480 0.0412
-4.500 -0.0653 0.03818 0.03084 -0.0610 0.6382 0.0405
-4.250 -0.0463 0.03555 0.02785 -0.0598 0.6281 0.0386
-4.000 -0.0255 0.03242 0.02398 -0.0577 0.6201 0.0356
-3.750 -0.0028 0.03066 0.02176 -0.0564 0.6106 0.0348
-3.500 0.0199 0.02892 0.01971 -0.0554 0.6019 0.0345
-3.250 0.0436 0.02734 0.01777 -0.0544 0.5933 0.0345
-3.000 0.0683 0.02597 0.01604 -0.0535 0.5847 0.0346
-2.750 0.0930 0.02470 0.01453 -0.0528 0.5769 0.0359
-2.500 0.1182 0.02382 0.01353 -0.0522 0.5686 0.0375
-2.250 0.1446 0.02286 0.01233 -0.0516 0.5616 0.0382
-2.000 0.1713 0.02195 0.01124 -0.0510 0.5540 0.0387
-1.750 0.1977 0.02117 0.01030 -0.0504 0.5471 0.0394
-1.500 0.2236 0.02050 0.00954 -0.0498 0.5401 0.0403
-1.250 0.2487 0.01993 0.00888 -0.0490 0.5334 0.0416
-1.000 0.2733 0.01951 0.00834 -0.0481 0.5277 0.0440
-0.750 0.2972 0.01913 0.00797 -0.0474 0.5212 0.0480
-0.500 0.3219 0.01886 0.00756 -0.0465 0.5158 0.0517
-0.250 0.3469 0.01862 0.00721 -0.0458 0.5097 0.0564
0.000 0.3726 0.01842 0.00693 -0.0452 0.5039 0.0682
0.500 0.5360 0.01616 0.00682 -0.0659 0.4890 1.0000
0.750 0.5587 0.01632 0.00677 -0.0650 0.4847 1.0000
1.000 0.5809 0.01650 0.00685 -0.0640 0.4795 1.0000
1.250 0.6032 0.01669 0.00693 -0.0631 0.4747 1.0000
1.500 0.6260 0.01688 0.00697 -0.0622 0.4707 1.0000
1.750 0.6484 0.01710 0.00709 -0.0612 0.4665 1.0000
2.000 0.6704 0.01733 0.00728 -0.0603 0.4616 1.0000
2.250 0.6929 0.01756 0.00740 -0.0593 0.4574 1.0000
2.500 0.7160 0.01778 0.00750 -0.0585 0.4541 1.0000
2.750 0.7377 0.01807 0.00779 -0.0575 0.4497 1.0000
3.000 0.7597 0.01835 0.00805 -0.0565 0.4455 1.0000
3.250 0.7823 0.01861 0.00824 -0.0556 0.4417 1.0000
3.500 0.8057 0.01887 0.00839 -0.0549 0.4386 1.0000
3.750 0.8265 0.01922 0.00880 -0.0538 0.4342 1.0000
4.000 0.8483 0.01955 0.00916 -0.0528 0.4303 1.0000
4.250 0.8708 0.01985 0.00942 -0.0520 0.4269 1.0000
4.500 0.8944 0.02013 0.00962 -0.0513 0.4239 1.0000
4.750 0.9147 0.02054 0.01012 -0.0501 0.4197 1.0000
5.000 0.9356 0.02092 0.01057 -0.0491 0.4158 1.0000
5.250 0.9578 0.02127 0.01092 -0.0482 0.4125 1.0000
5.500 0.9812 0.02158 0.01119 -0.0476 0.4096 1.0000
5.750 1.0016 0.02202 0.01172 -0.0465 0.4059 1.0000
6.000 1.0211 0.02249 0.01230 -0.0453 0.4018 1.0000
6.250 1.0423 0.02290 0.01275 -0.0444 0.3984 1.0000
6.500 1.0652 0.02324 0.01309 -0.0437 0.3954 1.0000
6.750 1.0871 0.02365 0.01356 -0.0428 0.3923 1.0000
7.000 1.1041 0.02425 0.01433 -0.0414 0.3879 1.0000
7.250 1.1241 0.02473 0.01490 -0.0403 0.3843 1.0000
7.500 1.1465 0.02510 0.01530 -0.0396 0.3811 1.0000
7.750 1.1700 0.02545 0.01569 -0.0391 0.3782 1.0000
8.000 1.1836 0.02622 0.01668 -0.0373 0.3736 1.0000
8.250 1.2020 0.02675 0.01734 -0.0361 0.3695 1.0000
8.500 1.2243 0.02709 0.01772 -0.0354 0.3661 1.0000
8.750 1.2454 0.02752 0.01824 -0.0345 0.3627 1.0000
9.000 1.2564 0.02837 0.01932 -0.0325 0.3576 1.0000
9.250 1.2748 0.02882 0.01987 -0.0313 0.3533 1.0000
9.500 1.2997 0.02898 0.02005 -0.0310 0.3498 1.0000
9.750 1.3070 0.02993 0.02127 -0.0285 0.3444 1.0000
10.000 1.3207 0.03052 0.02200 -0.0268 0.3395 1.0000
10.250 1.3448 0.03060 0.02211 -0.0263 0.3354 1.0000
10.500 1.3477 0.03165 0.02339 -0.0235 0.3299 1.0000
10.750 1.3571 0.03232 0.02421 -0.0213 0.3246 1.0000
11.000 1.3825 0.03222 0.02413 -0.0209 0.3201 1.0000
11.250 1.3684 0.03382 0.02599 -0.0161 0.3145 1.0000
11.500 1.3736 0.03454 0.02683 -0.0137 0.3092 1.0000
11.750 1.3852 0.03503 0.02740 -0.0120 0.3043 1.0000
12.000 1.3655 0.03743 0.03002 -0.0085 0.2984 1.0000
12.250 1.3790 0.03784 0.03049 -0.0073 0.2927 1.0000
12.500 1.3545 0.04132 0.03416 -0.0052 0.2867 1.0000
12.750 1.3495 0.04352 0.03647 -0.0043 0.2801 1.0000
13.000 1.3286 0.04762 0.04071 -0.0039 0.2737 1.0000
13.250 1.3086 0.05205 0.04525 -0.0040 0.2664 1.0000
13.500 1.2591 0.06063 0.05392 -0.0057 0.2579 1.0000
13.750 1.2760 0.06088 0.05426 -0.0052 0.2512 1.0000
14.000 1.2156 0.07183 0.06525 -0.0081 0.2405 1.0000
14.250 1.2559 0.06871 0.06223 -0.0064 0.2355 1.0000
14.500 1.2118 0.07786 0.07144 -0.0091 0.2249 1.0000
14.750 1.1883 0.08438 0.07804 -0.0110 0.2153 1.0000
15.000 1.2188 0.08250 0.07623 -0.0098 0.2097 1.0000
15.250 1.1909 0.08993 0.08373 -0.0121 0.1998 1.0000
15.500 1.2047 0.09070 0.08456 -0.0120 0.1928 1.0000
15.750 1.2008 0.09442 0.08834 -0.0130 0.1843 1.0000
16.000 1.1945 0.09861 0.09261 -0.0143 0.1762 1.0000
16.250 1.2170 0.09785 0.09183 -0.0136 0.1686 1.0000
16.500 1.1973 0.10448 0.09858 -0.0160 0.1602 1.0000
16.750 1.2037 0.10654 0.10065 -0.0165 0.1525 1.0000
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Polar data table (+)
Polar graphs
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