EPPLER 333 AIRFOIL (e333-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 333 AIRFOIL (e333-il) Reynolds number: 100,000 Max Cl/Cd: 47.96 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e333-il-100000-n5.txt Download as CSV file: xf-e333-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 333 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3696 0.11140 0.10659 -0.0206 1.0000 0.0414
-9.500 -0.3669 0.10808 0.10332 -0.0224 1.0000 0.0415
-9.250 -0.3740 0.10491 0.10023 -0.0274 1.0000 0.0419
-8.750 -0.3570 0.09634 0.09176 -0.0248 1.0000 0.0436
-8.500 -0.3522 0.09311 0.08859 -0.0253 1.0000 0.0444
-8.250 -0.3490 0.08993 0.08547 -0.0259 1.0000 0.0456
-8.000 -0.3499 0.08647 0.08207 -0.0274 1.0000 0.0471
-7.750 -0.3541 0.08307 0.07875 -0.0293 1.0000 0.0476
-7.500 -0.3611 0.08001 0.07576 -0.0299 1.0000 0.0481
-7.250 -0.3660 0.07707 0.07287 -0.0302 1.0000 0.0486
-7.000 -0.3707 0.07399 0.06982 -0.0302 1.0000 0.0498
-6.750 -0.3746 0.07110 0.06694 -0.0300 0.9991 0.0510
-6.500 -0.3582 0.06821 0.06343 -0.0368 0.9446 0.0538
-6.250 -0.3347 0.06121 0.05647 -0.0403 0.9151 0.0549
-6.000 -0.3082 0.05652 0.05168 -0.0431 0.8848 0.0560
-5.750 -0.2821 0.05005 0.04465 -0.0438 0.8578 0.0310
-5.250 -0.2487 0.04187 0.03550 -0.0415 0.8081 0.0239
-5.000 -0.2324 0.03925 0.03263 -0.0404 0.7862 0.0234
-4.750 -0.2149 0.03681 0.02986 -0.0390 0.7669 0.0230
-4.500 -0.1966 0.03432 0.02697 -0.0373 0.7492 0.0225
-4.250 -0.1768 0.03199 0.02423 -0.0357 0.7328 0.0221
-4.000 -0.1551 0.02980 0.02159 -0.0342 0.7177 0.0218
-3.750 -0.1318 0.02780 0.01916 -0.0328 0.7032 0.0216
-3.250 -0.0811 0.02436 0.01491 -0.0306 0.6761 0.0219
-3.000 -0.0541 0.02307 0.01323 -0.0297 0.6630 0.0236
-2.750 -0.0277 0.02188 0.01184 -0.0291 0.6505 0.0252
-2.500 -0.0015 0.02095 0.01078 -0.0285 0.6388 0.0273
-2.250 0.0247 0.01999 0.00966 -0.0277 0.6280 0.0290
-2.000 0.0495 0.01917 0.00870 -0.0267 0.6167 0.0313
-1.750 0.0727 0.01849 0.00800 -0.0257 0.6061 0.0368
-1.500 0.0963 0.01794 0.00729 -0.0245 0.5968 0.0438
-1.250 0.1204 0.01741 0.00675 -0.0235 0.5867 0.0626
-0.750 0.3412 0.01535 0.00676 -0.0523 0.5577 1.0000
-0.500 0.3642 0.01539 0.00659 -0.0515 0.5494 1.0000
-0.250 0.3873 0.01544 0.00646 -0.0507 0.5408 1.0000
0.000 0.4104 0.01551 0.00636 -0.0499 0.5329 1.0000
0.250 0.4336 0.01558 0.00628 -0.0492 0.5253 1.0000
0.500 0.4569 0.01567 0.00624 -0.0484 0.5179 1.0000
0.750 0.4800 0.01577 0.00621 -0.0477 0.5106 1.0000
1.000 0.5033 0.01588 0.00620 -0.0469 0.5039 1.0000
1.250 0.5266 0.01600 0.00624 -0.0462 0.4968 1.0000
1.500 0.5499 0.01613 0.00625 -0.0454 0.4909 1.0000
1.750 0.5730 0.01627 0.00635 -0.0447 0.4838 1.0000
2.000 0.5962 0.01642 0.00640 -0.0439 0.4783 1.0000
2.250 0.6194 0.01659 0.00654 -0.0432 0.4718 1.0000
2.500 0.6423 0.01675 0.00667 -0.0424 0.4659 1.0000
2.750 0.6653 0.01694 0.00678 -0.0416 0.4606 1.0000
3.000 0.6879 0.01714 0.00700 -0.0408 0.4542 1.0000
3.250 0.7107 0.01734 0.00716 -0.0399 0.4490 1.0000
3.500 0.7331 0.01757 0.00739 -0.0391 0.4435 1.0000
3.750 0.7554 0.01780 0.00764 -0.0382 0.4378 1.0000
4.000 0.7780 0.01802 0.00781 -0.0373 0.4331 1.0000
4.250 0.7996 0.01829 0.00814 -0.0364 0.4272 1.0000
4.500 0.8214 0.01854 0.00844 -0.0354 0.4217 1.0000
4.750 0.8439 0.01879 0.00863 -0.0345 0.4175 1.0000
5.000 0.8644 0.01910 0.00906 -0.0334 0.4112 1.0000
5.250 0.8858 0.01937 0.00936 -0.0324 0.4060 1.0000
5.500 0.9074 0.01965 0.00967 -0.0313 0.4014 1.0000
5.750 0.9272 0.02000 0.01013 -0.0301 0.3954 1.0000
6.000 0.9481 0.02028 0.01044 -0.0290 0.3904 1.0000
6.250 0.9683 0.02060 0.01086 -0.0278 0.3851 1.0000
6.500 0.9874 0.02096 0.01132 -0.0264 0.3792 1.0000
6.750 1.0081 0.02123 0.01160 -0.0253 0.3743 1.0000
7.000 1.0259 0.02162 0.01215 -0.0237 0.3680 1.0000
7.250 1.0448 0.02195 0.01257 -0.0223 0.3623 1.0000
7.500 1.0640 0.02226 0.01294 -0.0209 0.3570 1.0000
7.750 1.0803 0.02267 0.01351 -0.0192 0.3501 1.0000
8.000 1.0997 0.02293 0.01379 -0.0178 0.3447 1.0000
8.250 1.1145 0.02338 0.01446 -0.0158 0.3376 1.0000
8.500 1.1322 0.02367 0.01481 -0.0142 0.3313 1.0000
8.750 1.1468 0.02411 0.01541 -0.0122 0.3242 1.0000
9.000 1.1630 0.02442 0.01580 -0.0104 0.3172 1.0000
9.250 1.1767 0.02488 0.01644 -0.0083 0.3097 1.0000
9.500 1.1920 0.02521 0.01685 -0.0065 0.3024 1.0000
9.750 1.2042 0.02572 0.01754 -0.0043 0.2940 1.0000
10.000 1.2186 0.02606 0.01793 -0.0024 0.2863 1.0000
10.250 1.2290 0.02664 0.01870 -0.0001 0.2769 1.0000
10.500 1.2397 0.02719 0.01937 0.0021 0.2678 1.0000
10.750 1.2499 0.02770 0.01996 0.0044 0.2589 1.0000
11.000 1.2559 0.02848 0.02090 0.0069 0.2488 1.0000
11.250 1.2591 0.02928 0.02180 0.0099 0.2394 1.0000
11.500 1.2609 0.03017 0.02274 0.0127 0.2302 1.0000
11.750 1.2609 0.03137 0.02405 0.0152 0.2205 1.0000
12.000 1.2596 0.03286 0.02565 0.0172 0.2109 1.0000
12.250 1.2569 0.03463 0.02748 0.0188 0.2017 1.0000
12.500 1.2524 0.03678 0.02969 0.0199 0.1925 1.0000
12.750 1.2464 0.03937 0.03239 0.0204 0.1831 1.0000
13.000 1.2396 0.04222 0.03530 0.0207 0.1747 1.0000
13.250 1.2313 0.04543 0.03859 0.0205 0.1663 1.0000
13.500 1.2224 0.04894 0.04220 0.0201 0.1582 1.0000
13.750 1.2130 0.05255 0.04582 0.0195 0.1509 1.0000
14.000 1.2026 0.05655 0.04992 0.0187 0.1432 1.0000
14.250 1.1931 0.06044 0.05384 0.0178 0.1365 1.0000
14.500 1.1824 0.06466 0.05815 0.0167 0.1297 1.0000
14.750 1.1737 0.06865 0.06218 0.0156 0.1236 1.0000
15.000 1.1643 0.07301 0.06662 0.0142 0.1172 1.0000
15.250 1.1563 0.07723 0.07086 0.0129 0.1112 1.0000
15.500 1.1476 0.08172 0.07545 0.0113 0.1052 1.0000
15.750 1.1410 0.08590 0.07963 0.0099 0.0998 1.0000
16.000 1.1334 0.09050 0.08436 0.0082 0.0944 1.0000
16.250 1.1284 0.09450 0.08830 0.0067 0.0894 1.0000
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Polar data table (+)
Polar graphs
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