EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 639 AIRFOIL (e639-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.86 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e639-il-1000000.txt Download as CSV file: xf-e639-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.1876 0.08937 0.08680 -0.0551 0.7312 0.0108
-9.250 -0.1832 0.08699 0.08433 -0.0556 0.7068 0.0113
-9.000 -0.1813 0.08384 0.08113 -0.0567 0.6892 0.0110
-8.750 -0.1782 0.08113 0.07836 -0.0576 0.6721 0.0114
-8.500 -0.1768 0.07810 0.07529 -0.0588 0.6582 0.0118
-8.250 -0.1765 0.07498 0.07215 -0.0600 0.6458 0.0122
-8.000 -0.1804 0.07146 0.06861 -0.0619 0.6349 0.0126
-7.750 -0.1983 0.06704 0.06418 -0.0649 0.6264 0.0130
-7.500 -0.1997 0.06299 0.06008 -0.0667 0.6174 0.0130
-7.250 -0.1964 0.05935 0.05635 -0.0679 0.6077 0.0131
-7.000 -0.1915 0.05546 0.05237 -0.0686 0.5992 0.0131
-6.750 -0.1848 0.05166 0.04844 -0.0687 0.5906 0.0131
-6.500 -0.1762 0.04768 0.04432 -0.0685 0.5825 0.0132
-6.250 -0.1770 0.04306 0.03955 -0.0677 0.5748 0.0135
-6.000 -0.1633 0.04110 0.03750 -0.0672 0.5658 0.0137
-5.750 -0.1483 0.03901 0.03528 -0.0665 0.5565 0.0139
-5.500 -0.1322 0.03690 0.03303 -0.0657 0.5474 0.0142
-5.250 -0.1152 0.03466 0.03064 -0.0648 0.5397 0.0148
-5.000 -0.0935 0.03068 0.02627 -0.0624 0.5329 0.0167
-4.750 -0.0857 0.02555 0.02069 -0.0596 0.5273 0.0170
-4.500 -0.0665 0.02391 0.01895 -0.0587 0.5196 0.0174
-4.250 -0.0452 0.02281 0.01772 -0.0579 0.5117 0.0177
-4.000 -0.0229 0.02170 0.01648 -0.0571 0.5041 0.0181
-3.750 -0.0003 0.02054 0.01513 -0.0562 0.4966 0.0188
-3.500 0.0270 0.02025 0.01455 -0.0550 0.4894 0.0211
-3.250 0.0449 0.01700 0.01097 -0.0533 0.4834 0.0222
-3.000 0.0699 0.01624 0.01014 -0.0528 0.4773 0.0228
-2.750 0.0953 0.01561 0.00940 -0.0523 0.4709 0.0242
-2.500 0.1236 0.01642 0.01004 -0.0518 0.4647 0.0266
-2.250 0.1478 0.01261 0.00589 -0.0503 0.4598 0.0200
-2.000 0.1737 0.01178 0.00493 -0.0496 0.4538 0.0195
-1.750 0.2002 0.01136 0.00445 -0.0492 0.4488 0.0199
-1.500 0.2259 0.01083 0.00386 -0.0485 0.4438 0.0198
-1.250 0.2513 0.01046 0.00343 -0.0479 0.4389 0.0200
-1.000 0.2772 0.01020 0.00312 -0.0473 0.4345 0.0205
-0.750 0.3035 0.01000 0.00290 -0.0469 0.4298 0.0210
-0.500 0.3292 0.00981 0.00265 -0.0463 0.4250 0.0213
-0.250 0.3544 0.00955 0.00234 -0.0457 0.4207 0.0219
0.000 0.3808 0.00938 0.00216 -0.0453 0.4172 0.0232
0.250 0.4075 0.00929 0.00205 -0.0450 0.4132 0.0246
0.500 0.4340 0.00924 0.00196 -0.0446 0.4090 0.0260
0.750 0.4607 0.00920 0.00188 -0.0443 0.4052 0.0286
1.000 0.4875 0.00909 0.00185 -0.0440 0.4017 0.0513
1.250 0.4877 0.00700 0.00188 -0.0390 0.3992 0.8014
1.500 0.5266 0.00695 0.00220 -0.0407 0.3952 0.9649
1.750 0.5800 0.00724 0.00240 -0.0460 0.3908 0.9773
2.000 0.6283 0.00742 0.00253 -0.0502 0.3873 0.9846
2.250 0.6951 0.00759 0.00262 -0.0585 0.3826 0.9900
2.500 0.7281 0.00769 0.00266 -0.0597 0.3791 0.9921
2.750 0.7584 0.00779 0.00272 -0.0604 0.3758 0.9940
3.000 0.7924 0.00780 0.00273 -0.0618 0.3729 0.9950
3.250 0.8258 0.00784 0.00274 -0.0632 0.3698 0.9962
3.500 0.8587 0.00790 0.00277 -0.0644 0.3666 0.9975
3.750 0.8910 0.00801 0.00284 -0.0656 0.3631 0.9989
4.000 0.9237 0.00807 0.00289 -0.0668 0.3604 1.0000
4.250 0.9475 0.00811 0.00294 -0.0661 0.3578 1.0000
4.500 0.9707 0.00818 0.00301 -0.0653 0.3552 1.0000
4.750 0.9936 0.00827 0.00309 -0.0644 0.3524 1.0000
5.000 1.0159 0.00839 0.00320 -0.0635 0.3494 1.0000
5.250 1.0383 0.00852 0.00332 -0.0625 0.3465 1.0000
5.500 1.0616 0.00859 0.00342 -0.0617 0.3442 1.0000
5.750 1.0846 0.00867 0.00352 -0.0609 0.3416 1.0000
6.000 1.1073 0.00877 0.00362 -0.0600 0.3385 1.0000
6.250 1.1292 0.00892 0.00376 -0.0589 0.3350 1.0000
6.500 1.1512 0.00907 0.00392 -0.0579 0.3317 1.0000
6.750 1.1744 0.00915 0.00403 -0.0571 0.3290 1.0000
7.000 1.1973 0.00925 0.00415 -0.0563 0.3255 1.0000
7.250 1.2192 0.00939 0.00430 -0.0553 0.3217 1.0000
7.500 1.2404 0.00958 0.00448 -0.0542 0.3176 1.0000
7.750 1.2637 0.00966 0.00461 -0.0534 0.3146 1.0000
8.000 1.2862 0.00978 0.00476 -0.0526 0.3110 1.0000
8.250 1.3077 0.00995 0.00494 -0.0515 0.3071 1.0000
8.500 1.3287 0.01015 0.00514 -0.0504 0.3030 1.0000
8.750 1.3516 0.01025 0.00529 -0.0497 0.2989 1.0000
9.000 1.3730 0.01042 0.00548 -0.0487 0.2935 1.0000
9.250 1.3937 0.01063 0.00570 -0.0475 0.2886 1.0000
9.500 1.4159 0.01077 0.00588 -0.0467 0.2827 1.0000
9.750 1.4354 0.01104 0.00612 -0.0454 0.2759 1.0000
10.000 1.4568 0.01122 0.00634 -0.0445 0.2684 1.0000
10.250 1.4757 0.01152 0.00662 -0.0432 0.2581 1.0000
10.500 1.4933 0.01187 0.00694 -0.0416 0.2459 1.0000
10.750 1.5098 0.01227 0.00730 -0.0399 0.2336 1.0000
11.000 1.5253 0.01272 0.00772 -0.0381 0.2203 1.0000
11.250 1.5386 0.01324 0.00819 -0.0360 0.2049 1.0000
11.500 1.5486 0.01389 0.00877 -0.0333 0.1867 1.0000
11.750 1.5496 0.01471 0.00947 -0.0291 0.1676 1.0000
12.000 1.5504 0.01555 0.01024 -0.0251 0.1506 1.0000
12.250 1.5507 0.01652 0.01114 -0.0213 0.1343 1.0000
12.500 1.5517 0.01756 0.01214 -0.0180 0.1213 1.0000
12.750 1.5514 0.01878 0.01334 -0.0149 0.1094 1.0000
13.000 1.5490 0.02029 0.01482 -0.0122 0.0979 1.0000
13.250 1.5459 0.02212 0.01664 -0.0101 0.0876 1.0000
13.500 1.5412 0.02436 0.01887 -0.0085 0.0780 1.0000
13.750 1.5357 0.02696 0.02147 -0.0075 0.0691 1.0000
14.000 1.5315 0.02968 0.02422 -0.0070 0.0620 1.0000
14.250 1.5241 0.03287 0.02743 -0.0066 0.0557 1.0000
14.500 1.5121 0.03664 0.03123 -0.0065 0.0491 1.0000
14.750 1.5053 0.03997 0.03463 -0.0066 0.0450 1.0000
15.000 1.4937 0.04385 0.03856 -0.0067 0.0411 1.0000
15.250 1.4800 0.04801 0.04277 -0.0069 0.0364 1.0000
15.500 1.4600 0.05299 0.04778 -0.0073 0.0310 1.0000
15.750 1.4487 0.05712 0.05198 -0.0078 0.0279 1.0000
16.000 1.4311 0.06211 0.05700 -0.0085 0.0236 1.0000
16.250 1.4160 0.06688 0.06182 -0.0093 0.0201 1.0000
16.500 1.3994 0.07196 0.06693 -0.0102 0.0159 1.0000
16.750 1.3820 0.07722 0.07222 -0.0112 0.0119 1.0000
17.000 1.3646 0.08261 0.07765 -0.0124 0.0084 1.0000
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Polar data table (+)
Polar graphs
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