EPPLER 642 AIRFOIL (e642-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 642 AIRFOIL (e642-il) Reynolds number: 1,000,000 Max Cl/Cd: 109.65 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e642-il-1000000-n5.txt Download as CSV file: xf-e642-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5999 0.05528 0.05205 -0.0917 0.7160 0.0062
-13.250 -0.6226 0.04847 0.04507 -0.0962 0.7121 0.0062
-13.000 -0.6589 0.04223 0.03859 -0.0977 0.7088 0.0063
-12.750 -0.6755 0.03889 0.03508 -0.0968 0.7052 0.0063
-12.500 -0.6895 0.03604 0.03205 -0.0949 0.7017 0.0063
-12.250 -0.7016 0.03355 0.02937 -0.0923 0.6979 0.0063
-11.750 -0.7134 0.02963 0.02510 -0.0866 0.6920 0.0064
-11.500 -0.7155 0.02793 0.02322 -0.0836 0.6894 0.0064
-11.250 -0.7120 0.02670 0.02186 -0.0808 0.6868 0.0064
-11.000 -0.7067 0.02567 0.02072 -0.0781 0.6842 0.0065
-10.750 -0.7025 0.02449 0.01938 -0.0749 0.6817 0.0065
-10.500 -0.6912 0.02367 0.01844 -0.0728 0.6794 0.0066
-10.250 -0.6782 0.02263 0.01727 -0.0710 0.6775 0.0066
-10.000 -0.6620 0.02186 0.01640 -0.0696 0.6757 0.0067
-9.750 -0.6457 0.02093 0.01534 -0.0682 0.6739 0.0068
-9.500 -0.6275 0.02014 0.01445 -0.0670 0.6720 0.0068
-9.250 -0.6085 0.01936 0.01356 -0.0659 0.6699 0.0069
-9.000 -0.5884 0.01869 0.01279 -0.0649 0.6679 0.0070
-8.750 -0.5675 0.01804 0.01204 -0.0641 0.6659 0.0071
-8.500 -0.5460 0.01745 0.01135 -0.0633 0.6641 0.0072
-8.250 -0.5242 0.01682 0.01063 -0.0625 0.6625 0.0073
-8.000 -0.5013 0.01628 0.01002 -0.0619 0.6613 0.0075
-7.750 -0.4785 0.01570 0.00937 -0.0613 0.6599 0.0076
-7.500 -0.4555 0.01513 0.00873 -0.0606 0.6585 0.0078
-7.250 -0.4322 0.01461 0.00814 -0.0600 0.6571 0.0080
-7.000 -0.4087 0.01412 0.00759 -0.0595 0.6556 0.0081
-6.750 -0.3849 0.01366 0.00708 -0.0589 0.6541 0.0082
-6.500 -0.3608 0.01327 0.00663 -0.0584 0.6526 0.0083
-6.250 -0.3361 0.01295 0.00626 -0.0580 0.6510 0.0085
-6.000 -0.3115 0.01262 0.00588 -0.0576 0.6494 0.0086
-5.750 -0.2878 0.01221 0.00541 -0.0570 0.6479 0.0088
-5.500 -0.2640 0.01176 0.00494 -0.0565 0.6468 0.0091
-5.250 -0.2390 0.01144 0.00460 -0.0561 0.6457 0.0093
-5.000 -0.2136 0.01116 0.00430 -0.0558 0.6445 0.0096
-4.750 -0.1879 0.01091 0.00404 -0.0556 0.6431 0.0098
-4.500 -0.1619 0.01068 0.00380 -0.0554 0.6416 0.0102
-4.250 -0.1359 0.01046 0.00355 -0.0552 0.6402 0.0105
-4.000 -0.1096 0.01027 0.00335 -0.0550 0.6387 0.0109
-3.750 -0.0832 0.01011 0.00316 -0.0549 0.6371 0.0114
-3.500 -0.0567 0.00995 0.00298 -0.0548 0.6356 0.0119
-3.250 -0.0305 0.00976 0.00276 -0.0546 0.6339 0.0128
-3.000 -0.0038 0.00963 0.00261 -0.0545 0.6321 0.0135
-2.750 0.0232 0.00949 0.00248 -0.0545 0.6308 0.0145
-2.500 0.0504 0.00936 0.00235 -0.0545 0.6293 0.0164
-2.250 0.0763 0.00910 0.00221 -0.0543 0.6277 0.0400
-2.000 0.1021 0.00884 0.00209 -0.0541 0.6259 0.0782
-1.750 0.1272 0.00853 0.00198 -0.0539 0.6242 0.1357
-1.500 0.1519 0.00819 0.00188 -0.0536 0.6224 0.2077
-1.250 0.1765 0.00785 0.00179 -0.0533 0.6206 0.2870
-1.000 0.1994 0.00736 0.00168 -0.0528 0.6188 0.4065
-0.750 0.2200 0.00665 0.00153 -0.0519 0.6168 0.5779
-0.500 0.2396 0.00603 0.00166 -0.0504 0.6152 0.7872
-0.250 0.2684 0.00612 0.00175 -0.0506 0.6134 0.8075
0.000 0.2971 0.00620 0.00184 -0.0508 0.6112 0.8180
0.250 0.3259 0.00629 0.00191 -0.0510 0.6088 0.8258
0.500 0.3543 0.00638 0.00198 -0.0512 0.6062 0.8315
0.750 0.3822 0.00650 0.00210 -0.0511 0.6037 0.8372
1.000 0.4106 0.00662 0.00218 -0.0513 0.6011 0.8426
1.250 0.4394 0.00664 0.00221 -0.0516 0.5984 0.8451
1.500 0.4683 0.00664 0.00222 -0.0520 0.5949 0.8460
1.750 0.4970 0.00665 0.00222 -0.0523 0.5911 0.8467
2.000 0.5254 0.00668 0.00221 -0.0526 0.5872 0.8472
2.250 0.5544 0.00669 0.00223 -0.0530 0.5833 0.8477
2.500 0.5832 0.00670 0.00224 -0.0534 0.5783 0.8482
2.750 0.6114 0.00673 0.00225 -0.0537 0.5730 0.8487
3.000 0.6399 0.00676 0.00228 -0.0540 0.5671 0.8493
3.250 0.6679 0.00680 0.00231 -0.0543 0.5595 0.8499
3.500 0.6959 0.00685 0.00234 -0.0545 0.5504 0.8505
3.750 0.7232 0.00693 0.00238 -0.0546 0.5386 0.8510
4.000 0.7499 0.00703 0.00244 -0.0546 0.5242 0.8515
4.250 0.7760 0.00717 0.00253 -0.0546 0.5084 0.8520
4.500 0.8015 0.00734 0.00263 -0.0544 0.4914 0.8525
4.750 0.8265 0.00754 0.00277 -0.0541 0.4737 0.8531
5.000 0.8509 0.00776 0.00293 -0.0538 0.4555 0.8537
5.250 0.8751 0.00799 0.00309 -0.0534 0.4371 0.8542
5.500 0.8986 0.00825 0.00328 -0.0529 0.4167 0.8548
5.750 0.9211 0.00855 0.00349 -0.0522 0.3953 0.8556
6.000 0.9435 0.00884 0.00372 -0.0516 0.3749 0.8563
6.250 0.9644 0.00919 0.00397 -0.0506 0.3518 0.8569
6.500 0.9841 0.00957 0.00425 -0.0495 0.3272 0.8575
6.750 0.9993 0.01011 0.00462 -0.0476 0.2928 0.8581
7.000 1.0136 0.01064 0.00500 -0.0455 0.2620 0.8587
7.250 1.0240 0.01123 0.00542 -0.0428 0.2290 0.8595
7.500 1.0316 0.01171 0.00579 -0.0394 0.2033 0.8605
7.750 1.0395 0.01227 0.00625 -0.0362 0.1801 0.8616
8.000 1.0510 0.01276 0.00669 -0.0337 0.1651 0.8624
8.250 1.0613 0.01332 0.00719 -0.0311 0.1494 0.8634
8.500 1.0665 0.01410 0.00786 -0.0280 0.1276 0.8645
8.750 1.0761 0.01476 0.00848 -0.0256 0.1141 0.8655
9.000 1.0827 0.01562 0.00927 -0.0231 0.0972 0.8666
9.250 1.0913 0.01646 0.01006 -0.0209 0.0848 0.8678
9.500 1.0986 0.01743 0.01098 -0.0188 0.0715 0.8690
9.750 1.1056 0.01849 0.01199 -0.0168 0.0588 0.8702
10.000 1.1132 0.01958 0.01303 -0.0150 0.0476 0.8712
10.250 1.1183 0.02087 0.01426 -0.0131 0.0344 0.8722
10.500 1.1263 0.02204 0.01539 -0.0116 0.0263 0.8730
10.750 1.1353 0.02318 0.01652 -0.0102 0.0200 0.8738
11.000 1.1398 0.02463 0.01793 -0.0085 0.0107 0.8749
11.250 1.1483 0.02584 0.01916 -0.0073 0.0081 0.8759
11.500 1.1597 0.02688 0.02024 -0.0063 0.0074 0.8770
11.750 1.1703 0.02801 0.02141 -0.0053 0.0067 0.8780
12.000 1.1818 0.02907 0.02252 -0.0045 0.0064 0.8790
12.250 1.1923 0.03024 0.02374 -0.0036 0.0061 0.8801
12.500 1.2023 0.03146 0.02501 -0.0028 0.0058 0.8812
12.750 1.2114 0.03279 0.02639 -0.0019 0.0055 0.8823
13.000 1.2204 0.03415 0.02780 -0.0011 0.0054 0.8834
13.250 1.2293 0.03555 0.02926 -0.0004 0.0052 0.8846
13.500 1.2360 0.03718 0.03095 0.0004 0.0050 0.8858
13.750 1.2454 0.03864 0.03247 0.0009 0.0049 0.8869
14.000 1.2542 0.04017 0.03406 0.0014 0.0048 0.8880
14.500 1.2687 0.04359 0.03762 0.0024 0.0047 0.8906
14.750 1.2765 0.04531 0.03940 0.0027 0.0047 0.8923
15.000 1.2824 0.04724 0.04142 0.0031 0.0045 0.8940
15.250 1.2889 0.04916 0.04341 0.0033 0.0045 0.8959
15.500 1.2940 0.05128 0.04561 0.0035 0.0043 0.8977
15.750 1.2987 0.05350 0.04791 0.0036 0.0042 0.8995
16.000 1.3036 0.05578 0.05026 0.0035 0.0041 0.9013
16.250 1.3060 0.05838 0.05295 0.0034 0.0041 0.9031
16.500 1.3103 0.06078 0.05543 0.0032 0.0039 0.9053
16.750 1.3133 0.06339 0.05813 0.0030 0.0039 0.9078
17.000 1.3132 0.06647 0.06130 0.0026 0.0039 0.9106
17.250 1.3153 0.06934 0.06426 0.0021 0.0038 0.9137
17.500 1.3150 0.07257 0.06758 0.0014 0.0037 0.9168
17.750 1.3138 0.07599 0.07111 0.0006 0.0037 0.9206
18.000 1.3099 0.07982 0.07506 -0.0003 0.0036 0.9257
18.250 1.3020 0.08439 0.07975 -0.0016 0.0035 0.9312
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