EPPLER 329 AIRFOIL (e329-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 329 AIRFOIL (e329-il) Reynolds number: 100,000 Max Cl/Cd: 47.1 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e329-il-100000-n5.txt Download as CSV file: xf-e329-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 329 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3544 0.09668 0.09201 -0.0425 1.0000 0.0477
-9.000 -0.3662 0.09276 0.08813 -0.0453 1.0000 0.0478
-8.750 -0.3801 0.08964 0.08504 -0.0456 1.0000 0.0478
-8.500 -0.3975 0.08720 0.08263 -0.0440 1.0000 0.0479
-8.250 -0.4106 0.08458 0.08001 -0.0423 1.0000 0.0479
-8.000 -0.4027 0.07999 0.07558 -0.0413 1.0000 0.0484
-7.750 -0.4053 0.07697 0.07263 -0.0396 1.0000 0.0487
-7.500 -0.4069 0.07381 0.06950 -0.0389 0.9968 0.0490
-7.000 -0.3816 0.06048 0.05573 -0.0443 0.9496 0.0269
-6.750 -0.3601 0.05645 0.05154 -0.0468 0.9273 0.0247
-6.500 -0.3422 0.04965 0.04413 -0.0486 0.9058 0.0213
-6.250 -0.3170 0.04594 0.04014 -0.0506 0.8844 0.0210
-6.000 -0.2924 0.04250 0.03635 -0.0518 0.8618 0.0205
-5.750 -0.2692 0.03921 0.03262 -0.0520 0.8399 0.0201
-5.500 -0.2481 0.03626 0.02922 -0.0513 0.8183 0.0198
-5.250 -0.2276 0.03361 0.02609 -0.0501 0.7982 0.0198
-5.000 -0.2061 0.03108 0.02297 -0.0486 0.7797 0.0209
-4.750 -0.1827 0.02895 0.02027 -0.0473 0.7622 0.0216
-4.500 -0.1589 0.02775 0.01893 -0.0469 0.7450 0.0228
-4.250 -0.1334 0.02620 0.01702 -0.0461 0.7294 0.0235
-4.000 -0.1064 0.02463 0.01510 -0.0454 0.7147 0.0241
-3.750 -0.0785 0.02320 0.01337 -0.0447 0.7009 0.0250
-3.500 -0.0508 0.02203 0.01193 -0.0441 0.6878 0.0259
-3.250 -0.0252 0.02108 0.01090 -0.0435 0.6746 0.0273
-3.000 -0.0006 0.02043 0.01016 -0.0427 0.6618 0.0310
-2.750 0.0226 0.01971 0.00938 -0.0417 0.6503 0.0347
-2.500 0.0456 0.01913 0.00864 -0.0404 0.6397 0.0393
-2.250 0.0679 0.01862 0.00808 -0.0393 0.6283 0.0477
-2.000 0.0903 0.01806 0.00753 -0.0380 0.6183 0.0637
-1.750 0.1117 0.01737 0.00704 -0.0367 0.6087 0.1215
-1.500 0.1128 0.01581 0.00819 -0.0292 0.6007 0.8052
-1.250 0.1514 0.01722 0.00934 -0.0273 0.5912 0.8854
-1.000 0.2622 0.01820 0.00979 -0.0406 0.5769 0.9356
-0.750 0.2923 0.01815 0.00953 -0.0412 0.5677 0.9397
-0.500 0.3222 0.01810 0.00926 -0.0418 0.5594 0.9426
-0.250 0.3492 0.01806 0.00908 -0.0419 0.5507 0.9460
0.000 0.3726 0.01807 0.00891 -0.0413 0.5434 0.9496
0.250 0.3983 0.01806 0.00878 -0.0411 0.5356 0.9525
0.500 0.4277 0.01805 0.00863 -0.0417 0.5284 0.9547
0.750 0.4553 0.01807 0.00853 -0.0419 0.5214 0.9572
1.000 0.4808 0.01810 0.00847 -0.0418 0.5141 0.9598
1.250 0.5046 0.01816 0.00840 -0.0412 0.5084 0.9627
1.500 0.5307 0.01821 0.00842 -0.0412 0.5012 0.9649
1.750 0.5592 0.01826 0.00837 -0.0416 0.4953 0.9667
2.000 0.5868 0.01834 0.00839 -0.0419 0.4890 0.9689
2.250 0.6124 0.01843 0.00845 -0.0418 0.4828 0.9711
2.500 0.6375 0.01854 0.00847 -0.0416 0.4779 0.9733
2.750 0.6623 0.01867 0.00861 -0.0414 0.4717 0.9757
3.000 0.6902 0.01878 0.00871 -0.0418 0.4659 0.9774
3.500 0.7432 0.01907 0.00897 -0.0420 0.4549 0.9812
3.750 0.7692 0.01923 0.00913 -0.0420 0.4497 0.9836
4.000 0.7944 0.01940 0.00924 -0.0418 0.4453 0.9856
4.250 0.8206 0.01961 0.00955 -0.0421 0.4392 0.9873
4.500 0.8470 0.01979 0.00975 -0.0422 0.4339 0.9892
4.750 0.8743 0.01998 0.00988 -0.0425 0.4297 0.9912
5.000 0.8994 0.02025 0.01031 -0.0425 0.4237 0.9938
5.250 0.9257 0.02048 0.01059 -0.0427 0.4185 0.9960
5.500 0.9525 0.02069 0.01076 -0.0429 0.4142 0.9980
5.750 0.9755 0.02102 0.01126 -0.0426 0.4083 1.0000
6.000 0.9928 0.02130 0.01161 -0.0409 0.4034 1.0000
6.250 1.0115 0.02154 0.01183 -0.0395 0.3992 1.0000
6.500 1.0262 0.02190 0.01234 -0.0375 0.3941 1.0000
6.750 1.0410 0.02222 0.01276 -0.0355 0.3888 1.0000
7.000 1.0579 0.02246 0.01302 -0.0337 0.3844 1.0000
7.250 1.0712 0.02282 0.01349 -0.0315 0.3795 1.0000
7.500 1.0828 0.02317 0.01398 -0.0289 0.3739 1.0000
7.750 1.0975 0.02342 0.01426 -0.0268 0.3693 1.0000
8.000 1.1088 0.02377 0.01470 -0.0242 0.3644 1.0000
8.250 1.1176 0.02414 0.01521 -0.0211 0.3587 1.0000
8.500 1.1316 0.02439 0.01550 -0.0189 0.3538 1.0000
8.750 1.1425 0.02478 0.01601 -0.0164 0.3483 1.0000
9.000 1.1552 0.02517 0.01652 -0.0142 0.3420 1.0000
9.250 1.1751 0.02539 0.01673 -0.0131 0.3367 1.0000
9.500 1.1850 0.02598 0.01756 -0.0108 0.3294 1.0000
9.750 1.2029 0.02626 0.01788 -0.0095 0.3230 1.0000
10.000 1.2146 0.02684 0.01865 -0.0076 0.3158 1.0000
10.250 1.2298 0.02722 0.01909 -0.0060 0.3088 1.0000
10.500 1.2401 0.02783 0.01988 -0.0039 0.3012 1.0000
10.750 1.2519 0.02827 0.02039 -0.0020 0.2939 1.0000
11.000 1.2572 0.02901 0.02128 0.0007 0.2863 1.0000
11.250 1.2660 0.02957 0.02190 0.0028 0.2788 1.0000
11.500 1.2683 0.03060 0.02310 0.0053 0.2706 1.0000
11.750 1.2753 0.03139 0.02393 0.0072 0.2629 1.0000
12.000 1.2741 0.03282 0.02553 0.0093 0.2542 1.0000
12.250 1.2752 0.03421 0.02700 0.0110 0.2458 1.0000
12.500 1.2742 0.03591 0.02879 0.0123 0.2373 1.0000
12.750 1.2703 0.03807 0.03108 0.0133 0.2286 1.0000
13.000 1.2683 0.04018 0.03321 0.0141 0.2203 1.0000
13.250 1.2603 0.04311 0.03628 0.0144 0.2115 1.0000
13.500 1.2538 0.04607 0.03932 0.0145 0.2032 1.0000
13.750 1.2467 0.04919 0.04248 0.0143 0.1948 1.0000
14.000 1.2364 0.05296 0.04636 0.0138 0.1868 1.0000
14.250 1.2291 0.05635 0.04976 0.0133 0.1789 1.0000
14.500 1.2171 0.06059 0.05411 0.0124 0.1709 1.0000
14.750 1.2084 0.06447 0.05803 0.0115 0.1634 1.0000
15.000 1.1991 0.06858 0.06219 0.0104 0.1558 1.0000
15.250 1.1901 0.07284 0.06652 0.0092 0.1487 1.0000
15.500 1.1839 0.07669 0.07039 0.0080 0.1418 1.0000
15.750 1.1743 0.08133 0.07513 0.0064 0.1349 1.0000
16.000 1.1700 0.08507 0.07885 0.0052 0.1282 1.0000
16.250 1.1609 0.08987 0.08378 0.0034 0.1221 1.0000
16.500 1.1576 0.09359 0.08748 0.0021 0.1160 1.0000
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Polar data table (+)
Polar graphs
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