EPPLER 682 AIRFOIL (e682-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 682 AIRFOIL (e682-il) Reynolds number: 500,000 Max Cl/Cd: 91.18 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e682-il-500000.txt Download as CSV file: xf-e682-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 682 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2097 0.06861 0.06568 -0.0990 0.8202 0.0269
-10.750 -0.2342 0.06024 0.05724 -0.1049 0.8193 0.0269
-10.500 -0.2591 0.05435 0.05127 -0.1082 0.8181 0.0269
-10.250 -0.2827 0.04995 0.04678 -0.1091 0.8166 0.0269
-10.000 -0.3041 0.04643 0.04316 -0.1084 0.8150 0.0269
-9.750 -0.3267 0.04352 0.04013 -0.1063 0.8132 0.0269
-9.500 -0.3494 0.04124 0.03771 -0.1027 0.8113 0.0269
-9.250 -0.3852 0.03449 0.03082 -0.0987 0.8096 0.0275
-9.000 -0.3784 0.03200 0.02832 -0.0976 0.8084 0.0279
-8.750 -0.3742 0.02998 0.02624 -0.0959 0.8069 0.0283
-8.500 -0.3705 0.02802 0.02419 -0.0939 0.8053 0.0288
-8.250 -0.3648 0.02601 0.02209 -0.0921 0.8041 0.0295
-8.000 -0.3592 0.02388 0.01983 -0.0900 0.8028 0.0305
-7.750 -0.3502 0.02408 0.01963 -0.0865 0.8012 0.0337
-7.250 -0.3603 0.02394 0.01790 -0.0825 0.8007 0.0203
-7.000 -0.3386 0.02169 0.01538 -0.0817 0.7995 0.0195
-6.750 -0.3140 0.02001 0.01349 -0.0812 0.7981 0.0191
-6.500 -0.2879 0.01874 0.01205 -0.0810 0.7968 0.0189
-6.250 -0.2620 0.01784 0.01106 -0.0808 0.7956 0.0192
-6.000 -0.2366 0.01720 0.01035 -0.0806 0.7945 0.0198
-5.750 -0.2113 0.01648 0.00956 -0.0803 0.7933 0.0202
-5.500 -0.1870 0.01582 0.00883 -0.0798 0.7921 0.0203
-5.250 -0.1637 0.01529 0.00825 -0.0792 0.7909 0.0206
-5.000 -0.1409 0.01489 0.00780 -0.0784 0.7896 0.0211
-4.750 -0.1195 0.01437 0.00727 -0.0775 0.7882 0.0216
-4.500 -0.0986 0.01387 0.00675 -0.0765 0.7866 0.0225
-4.250 -0.0757 0.01354 0.00642 -0.0758 0.7849 0.0239
-4.000 -0.0518 0.01330 0.00616 -0.0753 0.7831 0.0255
-3.750 -0.0279 0.01304 0.00588 -0.0747 0.7814 0.0288
-3.500 -0.0043 0.01274 0.00562 -0.0741 0.7798 0.0396
-3.250 0.0132 0.01198 0.00535 -0.0727 0.7781 0.1481
-3.000 0.0302 0.01127 0.00516 -0.0712 0.7765 0.2854
-2.750 0.0425 0.01040 0.00501 -0.0691 0.7747 0.4754
-2.500 0.0495 0.00942 0.00513 -0.0652 0.7726 0.7196
-2.250 0.0741 0.00993 0.00575 -0.0640 0.7705 0.7993
-2.000 0.1004 0.01033 0.00611 -0.0634 0.7683 0.8181
-1.750 0.1268 0.01073 0.00647 -0.0627 0.7662 0.8314
-1.500 0.1520 0.01141 0.00716 -0.0610 0.7642 0.8433
-1.250 0.1784 0.01177 0.00749 -0.0600 0.7625 0.8507
-1.000 0.2060 0.01211 0.00778 -0.0594 0.7608 0.8571
-0.750 0.2324 0.01251 0.00814 -0.0584 0.7589 0.8652
-0.500 0.2586 0.01284 0.00848 -0.0575 0.7563 0.8717
-0.250 0.2823 0.01294 0.00857 -0.0566 0.7534 0.8786
0.000 0.3131 0.01306 0.00867 -0.0568 0.7510 0.8818
0.250 0.3420 0.01310 0.00868 -0.0569 0.7487 0.8860
0.500 0.3636 0.01303 0.00856 -0.0560 0.7465 0.8918
0.750 0.3957 0.01298 0.00846 -0.0567 0.7446 0.8933
1.000 0.4232 0.01297 0.00846 -0.0567 0.7416 0.8952
1.250 0.4490 0.01292 0.00843 -0.0564 0.7379 0.8977
1.500 0.4743 0.01281 0.00830 -0.0561 0.7347 0.9003
1.750 0.4988 0.01264 0.00811 -0.0557 0.7318 0.9029
2.000 0.5248 0.01253 0.00794 -0.0558 0.7293 0.9053
2.250 0.5469 0.01237 0.00782 -0.0548 0.7252 0.9067
2.500 0.5722 0.01221 0.00767 -0.0545 0.7210 0.9078
2.750 0.6003 0.01201 0.00747 -0.0547 0.7174 0.9087
3.000 0.6308 0.01183 0.00725 -0.0554 0.7144 0.9095
3.250 0.6527 0.01171 0.00718 -0.0544 0.7094 0.9108
3.500 0.6771 0.01153 0.00703 -0.0540 0.7045 0.9118
3.750 0.7057 0.01133 0.00681 -0.0544 0.7005 0.9128
4.000 0.7285 0.01119 0.00671 -0.0537 0.6950 0.9139
4.250 0.7529 0.01101 0.00656 -0.0533 0.6889 0.9147
4.500 0.7800 0.01082 0.00637 -0.0534 0.6834 0.9156
4.750 0.8015 0.01068 0.00629 -0.0525 0.6746 0.9167
5.000 0.8261 0.01052 0.00616 -0.0522 0.6659 0.9173
5.250 0.8510 0.01038 0.00603 -0.0520 0.6557 0.9179
5.500 0.8740 0.01030 0.00598 -0.0514 0.6428 0.9185
5.750 0.8971 0.01026 0.00592 -0.0508 0.6279 0.9194
6.000 0.9185 0.01026 0.00589 -0.0499 0.6101 0.9200
6.250 0.9363 0.01030 0.00589 -0.0482 0.5901 0.9206
6.500 0.9519 0.01044 0.00594 -0.0462 0.5695 0.9214
6.750 0.9646 0.01061 0.00605 -0.0436 0.5476 0.9222
7.000 0.9741 0.01081 0.00619 -0.0405 0.5266 0.9232
7.250 0.9822 0.01113 0.00645 -0.0371 0.5041 0.9248
7.500 0.9889 0.01161 0.00683 -0.0338 0.4786 0.9261
7.750 0.9938 0.01221 0.00732 -0.0305 0.4487 0.9274
8.000 0.9974 0.01296 0.00793 -0.0271 0.4172 0.9287
8.250 1.0019 0.01379 0.00864 -0.0242 0.3856 0.9300
8.500 1.0075 0.01469 0.00942 -0.0216 0.3552 0.9313
8.750 1.0170 0.01552 0.01015 -0.0197 0.3302 0.9323
9.000 1.0260 0.01641 0.01095 -0.0178 0.3047 0.9332
9.250 1.0329 0.01737 0.01179 -0.0156 0.2775 0.9346
9.500 1.0392 0.01836 0.01267 -0.0134 0.2505 0.9360
9.750 1.0482 0.01929 0.01351 -0.0117 0.2261 0.9371
10.000 1.0555 0.02036 0.01446 -0.0098 0.1986 0.9384
10.250 1.0630 0.02146 0.01543 -0.0080 0.1723 0.9396
10.500 1.0708 0.02259 0.01644 -0.0064 0.1482 0.9409
10.750 1.0779 0.02380 0.01752 -0.0048 0.1233 0.9423
11.000 1.0862 0.02498 0.01860 -0.0033 0.1012 0.9436
11.250 1.0941 0.02623 0.01975 -0.0019 0.0812 0.9449
11.500 1.0973 0.02784 0.02120 -0.0002 0.0551 0.9463
11.750 1.0981 0.02967 0.02287 0.0017 0.0320 0.9477
12.000 1.1003 0.03145 0.02457 0.0034 0.0203 0.9495
12.250 1.1098 0.03273 0.02591 0.0045 0.0179 0.9512
12.500 1.1159 0.03433 0.02755 0.0057 0.0158 0.9532
12.750 1.1255 0.03570 0.02902 0.0066 0.0149 0.9554
13.000 1.1343 0.03715 0.03055 0.0074 0.0140 0.9581
13.250 1.1410 0.03891 0.03239 0.0081 0.0133 0.9610
13.500 1.1476 0.04083 0.03439 0.0086 0.0128 0.9643
13.750 1.1490 0.04342 0.03709 0.0091 0.0123 0.9682
14.000 1.1579 0.04546 0.03923 0.0088 0.0121 0.9723
14.250 1.1657 0.04775 0.04164 0.0084 0.0118 0.9803
14.500 1.1699 0.05000 0.04399 0.0086 0.0116 1.0000
14.750 1.1734 0.05255 0.04664 0.0086 0.0112 1.0000
15.000 1.1766 0.05519 0.04937 0.0086 0.0111 1.0000
15.250 1.1798 0.05790 0.05218 0.0084 0.0110 1.0000
15.500 1.1821 0.06078 0.05514 0.0081 0.0107 1.0000
15.750 1.1845 0.06370 0.05815 0.0077 0.0106 1.0000
16.000 1.1868 0.06666 0.06120 0.0072 0.0104 1.0000
16.250 1.1878 0.06984 0.06447 0.0067 0.0102 1.0000
16.500 1.1890 0.07303 0.06774 0.0061 0.0100 1.0000
16.750 1.1907 0.07620 0.07099 0.0055 0.0100 1.0000
17.000 1.1928 0.07934 0.07422 0.0047 0.0099 1.0000
17.250 1.1939 0.08258 0.07754 0.0041 0.0097 1.0000
17.500 1.1958 0.08573 0.08078 0.0034 0.0096 1.0000
17.750 1.1974 0.08875 0.08391 0.0033 0.0094 1.0000
18.000 1.1979 0.09226 0.08756 0.0025 0.0094 1.0000
18.250 1.1972 0.09615 0.09158 0.0009 0.0093 1.0000
18.500 1.1937 0.10071 0.09630 -0.0013 0.0092 1.0000
18.750 1.1915 0.10495 0.10068 -0.0031 0.0091 1.0000
19.000 1.1879 0.10948 0.10537 -0.0051 0.0090 1.0000
19.250 1.1839 0.11409 0.11012 -0.0072 0.0091 1.0000
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Polar data table (+)
Polar graphs
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