EPPLER 639 AIRFOIL (e639-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 639 AIRFOIL (e639-il) Reynolds number: 500,000 Max Cl/Cd: 102.31 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e639-il-500000-n5.txt Download as CSV file: xf-e639-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2122 0.10432 0.10108 -0.0466 0.7333 0.0108
-10.250 -0.2081 0.10135 0.09803 -0.0477 0.7133 0.0126
-9.750 -0.2045 0.09450 0.09107 -0.0508 0.6809 0.0129
-8.750 -0.1561 0.07085 0.06738 -0.0510 0.6029 0.0131
-8.500 -0.1569 0.06685 0.06336 -0.0525 0.5955 0.0131
-8.250 -0.1608 0.06247 0.05899 -0.0542 0.5891 0.0132
-7.750 -0.2144 0.06621 0.06256 -0.0639 0.5956 0.0131
-7.250 -0.2103 0.05979 0.05602 -0.0651 0.5789 0.0129
-7.000 -0.2030 0.05775 0.05391 -0.0649 0.5697 0.0125
-6.750 -0.1980 0.05408 0.05014 -0.0655 0.5622 0.0123
-6.500 -0.1914 0.05000 0.04591 -0.0658 0.5555 0.0123
-6.250 -0.1816 0.04660 0.04236 -0.0656 0.5480 0.0121
-6.000 -0.1710 0.04259 0.03814 -0.0649 0.5419 0.0123
-5.750 -0.1584 0.03891 0.03425 -0.0640 0.5354 0.0123
-5.500 -0.1448 0.03510 0.03016 -0.0625 0.5294 0.0125
-5.250 -0.1311 0.02995 0.02459 -0.0602 0.5241 0.0130
-5.000 -0.1168 0.02600 0.02022 -0.0579 0.5180 0.0130
-4.750 -0.1010 0.02264 0.01637 -0.0558 0.5121 0.0132
-4.500 -0.0810 0.02078 0.01423 -0.0546 0.5049 0.0135
-4.250 -0.0584 0.01959 0.01283 -0.0537 0.4977 0.0137
-4.000 -0.0348 0.01846 0.01148 -0.0528 0.4907 0.0139
-3.500 0.0147 0.01680 0.00947 -0.0515 0.4784 0.0145
-3.250 0.0402 0.01610 0.00860 -0.0509 0.4722 0.0151
-3.000 0.0659 0.01531 0.00763 -0.0503 0.4665 0.0154
-2.750 0.0919 0.01456 0.00671 -0.0497 0.4605 0.0156
-2.500 0.1177 0.01396 0.00597 -0.0491 0.4548 0.0158
-2.250 0.1438 0.01345 0.00537 -0.0486 0.4499 0.0161
-2.000 0.1697 0.01306 0.00488 -0.0481 0.4449 0.0165
-1.750 0.1955 0.01274 0.00448 -0.0475 0.4402 0.0168
-1.500 0.2214 0.01248 0.00416 -0.0470 0.4357 0.0171
-1.250 0.2460 0.01202 0.00368 -0.0463 0.4310 0.0175
-1.000 0.2712 0.01176 0.00340 -0.0458 0.4263 0.0184
-0.750 0.2969 0.01160 0.00321 -0.0453 0.4224 0.0193
-0.500 0.3229 0.01142 0.00302 -0.0448 0.4185 0.0200
-0.250 0.3489 0.01128 0.00284 -0.0444 0.4144 0.0206
0.000 0.3750 0.01119 0.00270 -0.0440 0.4104 0.0213
0.250 0.4013 0.01113 0.00259 -0.0436 0.4067 0.0219
0.500 0.4277 0.01104 0.00248 -0.0432 0.4028 0.0235
0.750 0.4542 0.01099 0.00241 -0.0429 0.3992 0.0258
1.000 0.4804 0.01096 0.00238 -0.0425 0.3958 0.0346
1.250 0.5015 0.01033 0.00241 -0.0415 0.3928 0.2915
1.500 0.5260 0.00869 0.00271 -0.0407 0.3895 0.9411
1.750 0.5743 0.00892 0.00287 -0.0448 0.3853 0.9688
2.000 0.6310 0.00919 0.00303 -0.0508 0.3811 0.9838
2.250 0.6785 0.00931 0.00307 -0.0551 0.3777 0.9881
2.500 0.7099 0.00937 0.00311 -0.0560 0.3745 0.9900
2.750 0.7406 0.00945 0.00315 -0.0567 0.3710 0.9921
3.000 0.7704 0.00955 0.00321 -0.0572 0.3677 0.9940
3.250 0.8022 0.00966 0.00326 -0.0583 0.3648 0.9954
3.500 0.8338 0.00974 0.00332 -0.0593 0.3622 0.9970
3.750 0.8652 0.00981 0.00340 -0.0602 0.3591 0.9986
4.000 0.8967 0.00991 0.00348 -0.0612 0.3558 0.9999
4.250 0.9195 0.01002 0.00358 -0.0603 0.3530 1.0000
4.500 0.9417 0.01016 0.00369 -0.0593 0.3504 1.0000
4.750 0.9642 0.01029 0.00382 -0.0583 0.3479 1.0000
5.000 0.9870 0.01039 0.00395 -0.0574 0.3451 1.0000
5.250 1.0096 0.01051 0.00408 -0.0565 0.3423 1.0000
5.500 1.0319 0.01065 0.00423 -0.0556 0.3396 1.0000
5.750 1.0539 0.01081 0.00439 -0.0546 0.3369 1.0000
6.000 1.0757 0.01098 0.00455 -0.0535 0.3342 1.0000
6.250 1.0985 0.01110 0.00472 -0.0527 0.3315 1.0000
6.500 1.1209 0.01124 0.00490 -0.0517 0.3286 1.0000
6.750 1.1430 0.01140 0.00507 -0.0508 0.3253 1.0000
7.000 1.1645 0.01158 0.00526 -0.0497 0.3220 1.0000
7.250 1.1862 0.01176 0.00546 -0.0487 0.3189 1.0000
7.500 1.2086 0.01190 0.00566 -0.0478 0.3150 1.0000
7.750 1.2302 0.01208 0.00587 -0.0468 0.3109 1.0000
8.000 1.2509 0.01229 0.00608 -0.0457 0.3067 1.0000
8.250 1.2727 0.01246 0.00631 -0.0448 0.3024 1.0000
8.500 1.2942 0.01265 0.00655 -0.0438 0.2977 1.0000
8.750 1.3146 0.01288 0.00679 -0.0426 0.2932 1.0000
9.000 1.3354 0.01310 0.00706 -0.0416 0.2890 1.0000
9.250 1.3563 0.01331 0.00733 -0.0405 0.2839 1.0000
9.500 1.3749 0.01360 0.00762 -0.0391 0.2777 1.0000
9.750 1.3952 0.01383 0.00792 -0.0381 0.2710 1.0000
10.000 1.4126 0.01417 0.00826 -0.0365 0.2630 1.0000
10.250 1.4309 0.01449 0.00861 -0.0352 0.2538 1.0000
10.500 1.4471 0.01488 0.00901 -0.0335 0.2439 1.0000
10.750 1.4602 0.01539 0.00949 -0.0314 0.2299 1.0000
11.000 1.4697 0.01595 0.01003 -0.0287 0.2161 1.0000
11.250 1.4732 0.01670 0.01071 -0.0250 0.1985 1.0000
11.500 1.4735 0.01768 0.01160 -0.0213 0.1791 1.0000
11.750 1.4727 0.01882 0.01267 -0.0177 0.1608 1.0000
12.000 1.4668 0.02035 0.01413 -0.0141 0.1427 1.0000
12.250 1.4674 0.02174 0.01552 -0.0118 0.1317 1.0000
12.500 1.4650 0.02351 0.01729 -0.0097 0.1205 1.0000
12.750 1.4643 0.02541 0.01922 -0.0082 0.1126 1.0000
13.000 1.4583 0.02796 0.02178 -0.0071 0.1024 1.0000
13.250 1.4498 0.03100 0.02483 -0.0063 0.0924 1.0000
13.500 1.4424 0.03412 0.02798 -0.0059 0.0835 1.0000
13.750 1.4351 0.03737 0.03128 -0.0057 0.0775 1.0000
14.000 1.4252 0.04099 0.03494 -0.0056 0.0711 1.0000
14.250 1.4146 0.04475 0.03876 -0.0057 0.0653 1.0000
14.500 1.4067 0.04829 0.04237 -0.0059 0.0619 1.0000
14.750 1.3970 0.05207 0.04622 -0.0062 0.0589 1.0000
15.000 1.3833 0.05645 0.05065 -0.0067 0.0527 1.0000
15.250 1.3705 0.06086 0.05510 -0.0073 0.0484 1.0000
15.500 1.3548 0.06575 0.06001 -0.0082 0.0416 1.0000
15.750 1.3502 0.06935 0.06369 -0.0089 0.0407 1.0000
16.000 1.3341 0.07447 0.06882 -0.0100 0.0335 1.0000
16.250 1.3271 0.07852 0.07293 -0.0109 0.0309 1.0000
16.500 1.3132 0.08358 0.07800 -0.0122 0.0253 1.0000
16.750 1.3086 0.08739 0.08188 -0.0132 0.0234 1.0000
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Polar data table (+)
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