EPPLER 335 AIRFOIL (e335-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 335 AIRFOIL (e335-il) Reynolds number: 500,000 Max Cl/Cd: 72.04 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e335-il-500000-n5.txt Download as CSV file: xf-e335-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 335 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4253 0.08571 0.08355 -0.0074 0.8612 0.0067
-9.750 -0.4333 0.08112 0.07876 -0.0088 0.8032 0.0066
-9.500 -0.4430 0.07542 0.07297 -0.0116 0.7780 0.0065
-9.250 -0.5532 0.07251 0.07034 -0.0182 1.0000 0.0068
-9.000 -0.5671 0.06860 0.06638 -0.0184 0.9480 0.0067
-8.750 -0.5709 0.06414 0.06145 -0.0201 0.8146 0.0065
-8.500 -0.5858 0.06162 0.05869 -0.0162 0.7717 0.0064
-8.250 -0.6272 0.05099 0.04764 -0.0093 0.7599 0.0050
-8.000 -0.6290 0.04798 0.04438 -0.0061 0.7353 0.0049
-7.750 -0.6321 0.04423 0.04034 -0.0025 0.7152 0.0048
-7.500 -0.6315 0.04039 0.03619 0.0011 0.6978 0.0047
-7.250 -0.6277 0.03674 0.03221 0.0046 0.6816 0.0046
-7.000 -0.6278 0.03113 0.02607 0.0095 0.6696 0.0045
-6.750 -0.6212 0.02646 0.02081 0.0136 0.6568 0.0044
-6.500 -0.6061 0.02304 0.01682 0.0163 0.6434 0.0044
-6.250 -0.5849 0.02073 0.01407 0.0178 0.6293 0.0044
-6.000 -0.5610 0.01923 0.01224 0.0188 0.6150 0.0044
-5.750 -0.5358 0.01788 0.01061 0.0195 0.6017 0.0046
-5.500 -0.5107 0.01689 0.00941 0.0202 0.5895 0.0047
-5.000 -0.4611 0.01555 0.00776 0.0215 0.5650 0.0049
-4.750 -0.4376 0.01479 0.00691 0.0224 0.5537 0.0054
-4.500 -0.4134 0.01438 0.00642 0.0231 0.5427 0.0057
-4.250 -0.3893 0.01396 0.00591 0.0239 0.5321 0.0060
-4.000 -0.3651 0.01358 0.00545 0.0247 0.5227 0.0065
-3.750 -0.3411 0.01324 0.00502 0.0256 0.5129 0.0067
-3.500 -0.3170 0.01290 0.00461 0.0264 0.5032 0.0072
-3.250 -0.2925 0.01265 0.00431 0.0271 0.4939 0.0082
-3.000 -0.2677 0.01243 0.00404 0.0278 0.4849 0.0093
-2.750 -0.2434 0.01217 0.00374 0.0285 0.4773 0.0108
-2.500 -0.2190 0.01193 0.00344 0.0293 0.4690 0.0130
-2.250 -0.1946 0.01171 0.00319 0.0301 0.4613 0.0180
-2.000 -0.1706 0.01146 0.00299 0.0309 0.4533 0.0345
-1.750 -0.1473 0.01117 0.00282 0.0318 0.4464 0.0694
-1.500 -0.1248 0.01083 0.00267 0.0328 0.4396 0.1291
-1.250 -0.1136 0.00977 0.00241 0.0356 0.4340 0.3522
-1.000 -0.1149 0.00799 0.00271 0.0421 0.4292 0.8451
-0.750 -0.1016 0.00826 0.00292 0.0457 0.4228 0.8808
-0.500 -0.0800 0.00862 0.00320 0.0476 0.4172 0.8973
-0.250 -0.0351 0.00918 0.00369 0.0447 0.4102 0.9039
0.000 -0.0178 0.00939 0.00381 0.0472 0.4046 0.9135
0.250 0.0410 0.01005 0.00438 0.0413 0.3971 0.9163
0.500 0.0744 0.01015 0.00439 0.0402 0.3911 0.9172
0.750 0.1048 0.01021 0.00437 0.0396 0.3862 0.9182
1.000 0.1343 0.01025 0.00435 0.0393 0.3806 0.9193
1.250 0.1621 0.01029 0.00433 0.0392 0.3753 0.9207
1.500 0.1867 0.01033 0.00431 0.0399 0.3711 0.9227
2.000 0.2168 0.01023 0.00416 0.0452 0.3632 0.9295
2.250 0.2463 0.01029 0.00416 0.0448 0.3583 0.9300
2.500 0.2758 0.01034 0.00418 0.0443 0.3541 0.9306
2.750 0.3046 0.01037 0.00420 0.0440 0.3499 0.9312
3.000 0.3329 0.01042 0.00422 0.0438 0.3454 0.9318
3.250 0.3613 0.01051 0.00426 0.0436 0.3409 0.9326
3.500 0.3894 0.01055 0.00430 0.0434 0.3371 0.9334
3.750 0.4162 0.01059 0.00434 0.0435 0.3330 0.9342
4.000 0.4421 0.01065 0.00438 0.0438 0.3286 0.9352
4.250 0.4679 0.01072 0.00444 0.0441 0.3247 0.9364
4.500 0.4922 0.01076 0.00448 0.0447 0.3208 0.9378
4.750 0.5135 0.01078 0.00452 0.0459 0.3166 0.9394
5.000 0.5303 0.01080 0.00453 0.0480 0.3129 0.9417
5.250 0.5462 0.01082 0.00454 0.0504 0.3093 0.9441
5.500 0.5739 0.01087 0.00463 0.0502 0.3048 0.9446
5.750 0.6012 0.01096 0.00473 0.0501 0.3002 0.9451
6.000 0.6280 0.01107 0.00484 0.0501 0.2954 0.9456
6.250 0.6554 0.01115 0.00495 0.0499 0.2907 0.9462
6.500 0.6821 0.01125 0.00508 0.0499 0.2854 0.9468
6.750 0.7082 0.01138 0.00521 0.0500 0.2802 0.9475
7.000 0.7346 0.01148 0.00535 0.0500 0.2746 0.9482
7.250 0.7604 0.01162 0.00551 0.0501 0.2684 0.9491
7.500 0.7861 0.01176 0.00568 0.0503 0.2626 0.9501
7.750 0.8102 0.01190 0.00584 0.0507 0.2555 0.9512
8.000 0.8332 0.01205 0.00602 0.0514 0.2488 0.9524
8.250 0.8551 0.01221 0.00620 0.0522 0.2409 0.9538
8.500 0.8753 0.01237 0.00638 0.0534 0.2337 0.9554
8.750 0.8928 0.01254 0.00657 0.0551 0.2256 0.9573
9.000 0.9126 0.01272 0.00678 0.0563 0.2170 0.9587
9.250 0.9373 0.01301 0.00708 0.0564 0.2070 0.9594
9.500 0.9613 0.01335 0.00742 0.0565 0.1952 0.9603
9.750 0.9852 0.01372 0.00779 0.0566 0.1830 0.9612
10.000 1.0080 0.01413 0.00821 0.0569 0.1703 0.9624
10.250 1.0283 0.01462 0.00868 0.0575 0.1561 0.9638
10.500 1.0464 0.01517 0.00921 0.0585 0.1418 0.9655
10.750 1.0625 0.01572 0.00975 0.0598 0.1287 0.9676
11.000 1.0736 0.01630 0.01031 0.0620 0.1159 0.9704
11.250 1.0865 0.01703 0.01100 0.0635 0.1021 0.9727
11.500 1.1039 0.01786 0.01183 0.0639 0.0898 0.9742
11.750 1.1199 0.01865 0.01265 0.0645 0.0808 0.9762
12.000 1.1336 0.01957 0.01359 0.0651 0.0723 0.9786
12.250 1.1445 0.02068 0.01473 0.0657 0.0647 0.9818
12.500 1.1555 0.02209 0.01618 0.0654 0.0580 0.9845
12.750 1.1702 0.02370 0.01787 0.0639 0.0520 0.9861
13.000 1.1808 0.02582 0.02004 0.0621 0.0464 0.9882
13.250 1.1886 0.02825 0.02254 0.0602 0.0416 0.9907
13.500 1.1941 0.03089 0.02526 0.0584 0.0377 0.9934
13.750 1.1968 0.03409 0.02853 0.0561 0.0337 0.9963
14.000 1.1999 0.03737 0.03189 0.0537 0.0304 0.9987
14.250 1.1965 0.04098 0.03556 0.0518 0.0277 1.0000
14.500 1.1830 0.04376 0.03843 0.0533 0.0275 1.0000
14.750 1.1699 0.04694 0.04168 0.0540 0.0264 1.0000
15.000 1.1582 0.05033 0.04513 0.0541 0.0247 1.0000
15.250 1.1467 0.05390 0.04878 0.0539 0.0234 1.0000
15.500 1.1352 0.05769 0.05263 0.0533 0.0223 1.0000
15.750 1.1265 0.06135 0.05637 0.0526 0.0215 1.0000
16.000 1.1179 0.06515 0.06024 0.0517 0.0201 1.0000
16.250 1.1085 0.06916 0.06431 0.0507 0.0187 1.0000
16.500 1.0992 0.07327 0.06847 0.0495 0.0178 1.0000
16.750 1.0919 0.07720 0.07249 0.0483 0.0171 1.0000
17.000 1.0845 0.08121 0.07659 0.0471 0.0164 1.0000
17.250 1.0761 0.08543 0.08084 0.0457 0.0148 1.0000
17.500 1.0698 0.08944 0.08494 0.0443 0.0148 1.0000
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Polar data table (+)
Polar graphs
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