EPPLER 330 AIRFOIL (e330-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 330 AIRFOIL (e330-il) Reynolds number: 500,000 Max Cl/Cd: 71.86 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e330-il-500000-n5.txt Download as CSV file: xf-e330-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 330 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4557 0.08406 0.08217 0.0049 1.0000 0.0085
-9.000 -0.4629 0.07844 0.07656 0.0023 1.0000 0.0085
-8.750 -0.4740 0.07175 0.06972 -0.0020 0.8634 0.0084
-8.500 -0.5680 0.07357 0.07144 -0.0061 1.0000 0.0078
-8.250 -0.5790 0.06995 0.06778 -0.0050 1.0000 0.0078
-8.000 -0.5835 0.06594 0.06367 -0.0045 0.9379 0.0078
-7.750 -0.5838 0.06187 0.05917 -0.0038 0.8258 0.0079
-7.500 -0.5857 0.05851 0.05554 -0.0016 0.7849 0.0078
-7.250 -0.5849 0.05494 0.05173 0.0006 0.7571 0.0078
-7.000 -0.5823 0.05119 0.04772 0.0029 0.7350 0.0078
-6.750 -0.5936 0.04405 0.04026 0.0074 0.7204 0.0051
-6.500 -0.5878 0.04141 0.03736 0.0096 0.7013 0.0049
-6.250 -0.5792 0.03781 0.03346 0.0123 0.6855 0.0048
-6.000 -0.5691 0.03395 0.02924 0.0152 0.6701 0.0046
-5.750 -0.5567 0.03019 0.02509 0.0182 0.6566 0.0044
-5.500 -0.5430 0.02600 0.02040 0.0215 0.6438 0.0043
-5.250 -0.5251 0.02245 0.01634 0.0241 0.6314 0.0041
-5.000 -0.5030 0.01956 0.01294 0.0259 0.6186 0.0040
-4.750 -0.4780 0.01775 0.01075 0.0269 0.6048 0.0040
-4.500 -0.4524 0.01645 0.00919 0.0277 0.5917 0.0041
-4.250 -0.4268 0.01539 0.00792 0.0284 0.5792 0.0042
-4.000 -0.4017 0.01462 0.00699 0.0291 0.5670 0.0043
-3.750 -0.3771 0.01394 0.00617 0.0300 0.5548 0.0044
-3.500 -0.3527 0.01337 0.00548 0.0308 0.5435 0.0047
-3.250 -0.3282 0.01292 0.00492 0.0316 0.5327 0.0050
-3.000 -0.3040 0.01245 0.00437 0.0325 0.5221 0.0054
-2.750 -0.2792 0.01211 0.00396 0.0332 0.5112 0.0062
-2.500 -0.2541 0.01185 0.00362 0.0338 0.5014 0.0069
-2.250 -0.2286 0.01163 0.00334 0.0344 0.4917 0.0081
-2.000 -0.2035 0.01139 0.00305 0.0350 0.4824 0.0100
-1.750 -0.1783 0.01116 0.00277 0.0357 0.4733 0.0147
-1.500 -0.1533 0.01091 0.00255 0.0363 0.4644 0.0318
-1.250 -0.1301 0.01051 0.00237 0.0372 0.4563 0.0943
-1.000 -0.1068 0.01015 0.00224 0.0380 0.4482 0.1725
-0.750 -0.1075 0.00828 0.00187 0.0431 0.4426 0.5760
-0.500 -0.0908 0.00752 0.00228 0.0464 0.4356 0.8797
-0.250 -0.0650 0.00784 0.00253 0.0475 0.4283 0.9057
0.000 -0.0385 0.00807 0.00268 0.0482 0.4203 0.9171
0.250 -0.0010 0.00842 0.00292 0.0465 0.4128 0.9237
0.500 0.0234 0.00857 0.00300 0.0475 0.4060 0.9305
0.750 0.0569 0.00870 0.00304 0.0464 0.3990 0.9318
1.000 0.0900 0.00882 0.00308 0.0453 0.3919 0.9331
1.250 0.1221 0.00894 0.00313 0.0445 0.3857 0.9346
1.500 0.1519 0.00900 0.00314 0.0440 0.3791 0.9360
1.750 0.1802 0.00909 0.00315 0.0439 0.3729 0.9378
2.000 0.2051 0.00912 0.00316 0.0446 0.3674 0.9402
2.250 0.2216 0.00913 0.00313 0.0470 0.3622 0.9441
2.500 0.2549 0.00924 0.00319 0.0458 0.3561 0.9449
2.750 0.2881 0.00934 0.00327 0.0446 0.3501 0.9457
3.250 0.3504 0.00951 0.00338 0.0430 0.3387 0.9471
3.500 0.3822 0.00962 0.00346 0.0420 0.3327 0.9480
3.750 0.4158 0.00975 0.00357 0.0407 0.3272 0.9494
4.000 0.4470 0.00986 0.00367 0.0399 0.3209 0.9509
4.250 0.4741 0.00997 0.00375 0.0399 0.3155 0.9525
4.500 0.4983 0.01002 0.00383 0.0406 0.3100 0.9540
4.750 0.5148 0.01007 0.00388 0.0429 0.3048 0.9567
5.000 0.5370 0.01015 0.00395 0.0440 0.2994 0.9585
5.250 0.5669 0.01023 0.00405 0.0433 0.2932 0.9589
5.500 0.5959 0.01036 0.00417 0.0428 0.2866 0.9594
5.750 0.6250 0.01045 0.00429 0.0424 0.2802 0.9598
6.000 0.6533 0.01059 0.00442 0.0420 0.2731 0.9604
6.250 0.6818 0.01070 0.00457 0.0416 0.2656 0.9610
6.500 0.7097 0.01085 0.00473 0.0414 0.2577 0.9616
6.750 0.7373 0.01100 0.00489 0.0411 0.2492 0.9624
7.000 0.7645 0.01117 0.00508 0.0409 0.2405 0.9632
7.250 0.7914 0.01138 0.00530 0.0408 0.2312 0.9642
7.500 0.8178 0.01157 0.00551 0.0408 0.2214 0.9653
7.750 0.8424 0.01180 0.00574 0.0411 0.2102 0.9666
8.000 0.8655 0.01205 0.00600 0.0416 0.1989 0.9681
8.250 0.8853 0.01232 0.00628 0.0429 0.1872 0.9701
8.500 0.9028 0.01262 0.00656 0.0446 0.1746 0.9723
8.750 0.9298 0.01302 0.00694 0.0441 0.1577 0.9728
9.000 0.9561 0.01348 0.00737 0.0437 0.1415 0.9735
9.250 0.9821 0.01398 0.00785 0.0433 0.1264 0.9743
9.500 1.0073 0.01457 0.00842 0.0430 0.1102 0.9753
9.750 1.0313 0.01519 0.00901 0.0428 0.0941 0.9765
10.000 1.0534 0.01587 0.00965 0.0429 0.0792 0.9780
10.250 1.0745 0.01652 0.01030 0.0432 0.0679 0.9797
10.500 1.0939 0.01717 0.01096 0.0439 0.0592 0.9817
10.750 1.1081 0.01786 0.01165 0.0455 0.0515 0.9845
11.000 1.1310 0.01865 0.01246 0.0451 0.0434 0.9855
11.250 1.1535 0.01945 0.01333 0.0447 0.0371 0.9867
11.500 1.1737 0.02040 0.01431 0.0444 0.0315 0.9884
11.750 1.1930 0.02136 0.01533 0.0442 0.0268 0.9905
12.000 1.2091 0.02250 0.01651 0.0443 0.0225 0.9934
12.250 1.2215 0.02367 0.01775 0.0446 0.0193 0.9962
12.500 1.2327 0.02523 0.01940 0.0440 0.0166 0.9992
12.750 1.2265 0.02683 0.02109 0.0461 0.0152 1.0000
13.000 1.2149 0.02869 0.02304 0.0488 0.0148 1.0000
13.250 1.2058 0.03099 0.02541 0.0503 0.0138 1.0000
13.500 1.1979 0.03368 0.02817 0.0509 0.0129 1.0000
13.750 1.1903 0.03667 0.03124 0.0510 0.0120 1.0000
14.000 1.1845 0.03969 0.03437 0.0509 0.0114 1.0000
14.250 1.1785 0.04285 0.03764 0.0504 0.0108 1.0000
14.500 1.1703 0.04638 0.04124 0.0498 0.0099 1.0000
14.750 1.1590 0.05035 0.04526 0.0489 0.0087 1.0000
15.000 1.1522 0.05387 0.04892 0.0480 0.0092 1.0000
15.250 1.1394 0.05821 0.05331 0.0468 0.0079 1.0000
15.500 1.1313 0.06205 0.05725 0.0457 0.0076 1.0000
15.750 1.1231 0.06608 0.06136 0.0444 0.0072 1.0000
16.000 1.1139 0.07039 0.06578 0.0430 0.0071 1.0000
16.250 1.1049 0.07478 0.07026 0.0414 0.0067 1.0000
16.500 1.0934 0.07958 0.07510 0.0395 0.0056 1.0000
16.750 1.0862 0.08390 0.07953 0.0380 0.0059 1.0000
17.000 1.0759 0.08876 0.08445 0.0360 0.0050 1.0000
17.250 1.0669 0.09353 0.08932 0.0341 0.0051 1.0000
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