EPPLER 548 AIRFOIL (e548-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: EPPLER 548 AIRFOIL (e548-il) Reynolds number: 100,000 Max Cl/Cd: 38.56 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e548-il-100000-n5.txt Download as CSV file: xf-e548-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 548 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4937 0.09321 0.08807 -0.0496 1.0000 0.0190
-12.500 -0.5139 0.08546 0.08026 -0.0543 1.0000 0.0188
-12.250 -0.5340 0.07914 0.07385 -0.0576 1.0000 0.0186
-12.000 -0.5566 0.07342 0.06800 -0.0599 1.0000 0.0184
-11.750 -0.5773 0.06860 0.06305 -0.0609 1.0000 0.0183
-11.500 -0.6013 0.06391 0.05817 -0.0611 1.0000 0.0183
-11.250 -0.6180 0.06033 0.05443 -0.0603 1.0000 0.0182
-11.000 -0.6350 0.05695 0.05086 -0.0588 1.0000 0.0181
-10.750 -0.6513 0.05381 0.04751 -0.0566 1.0000 0.0181
-10.500 -0.6633 0.05122 0.04474 -0.0540 1.0000 0.0180
-10.250 -0.6758 0.04869 0.04199 -0.0507 1.0000 0.0181
-10.000 -0.6854 0.04658 0.03969 -0.0470 1.0000 0.0181
-9.750 -0.6939 0.04453 0.03744 -0.0430 1.0000 0.0182
-9.500 -0.6972 0.04249 0.03517 -0.0394 1.0000 0.0183
-9.250 -0.6783 0.03951 0.03182 -0.0397 0.9808 0.0186
-9.000 -0.6461 0.03636 0.02816 -0.0415 0.9551 0.0191
-8.750 -0.6038 0.03402 0.02567 -0.0452 0.9333 0.0199
-8.500 -0.5546 0.03188 0.02332 -0.0497 0.9118 0.0211
-8.250 -0.5046 0.03001 0.02117 -0.0540 0.8881 0.0234
-8.000 -0.4624 0.02862 0.01961 -0.0572 0.8612 0.0264
-7.750 -0.4301 0.02733 0.01818 -0.0584 0.8350 0.0286
-7.500 -0.4058 0.02636 0.01700 -0.0582 0.8115 0.0321
-7.250 -0.3871 0.02551 0.01608 -0.0574 0.7913 0.0357
-7.000 -0.3706 0.02468 0.01514 -0.0560 0.7736 0.0405
-6.750 -0.3552 0.02388 0.01427 -0.0544 0.7585 0.0479
-6.500 -0.3411 0.02311 0.01348 -0.0526 0.7448 0.0595
-6.250 -0.3280 0.02237 0.01283 -0.0505 0.7321 0.0783
-6.000 -0.3161 0.02161 0.01225 -0.0484 0.7209 0.1146
-5.750 -0.3086 0.02070 0.01168 -0.0457 0.7105 0.1782
-5.500 -0.3108 0.01949 0.01101 -0.0418 0.7006 0.2741
-5.250 -0.2851 0.02074 0.01393 -0.0369 0.6924 0.5536
-5.000 -0.2829 0.02033 0.01336 -0.0336 0.6833 0.6058
-4.750 -0.2735 0.02032 0.01311 -0.0308 0.6760 0.6385
-4.500 -0.2460 0.02140 0.01402 -0.0292 0.6677 0.6602
-4.250 -0.2186 0.02228 0.01468 -0.0277 0.6605 0.6768
-4.000 -0.1874 0.02345 0.01569 -0.0264 0.6531 0.6933
-3.750 -0.1510 0.02482 0.01688 -0.0254 0.6459 0.7094
-3.500 -0.1273 0.02516 0.01704 -0.0240 0.6402 0.7215
-3.250 -0.0979 0.02525 0.01699 -0.0239 0.6335 0.7251
-3.000 -0.0766 0.02507 0.01663 -0.0231 0.6282 0.7306
-2.750 -0.0614 0.02468 0.01608 -0.0217 0.6234 0.7370
-2.500 -0.0344 0.02463 0.01593 -0.0215 0.6174 0.7393
-2.250 -0.0090 0.02453 0.01567 -0.0212 0.6121 0.7423
-2.000 0.0129 0.02431 0.01530 -0.0206 0.6081 0.7462
-1.750 0.0250 0.02384 0.01476 -0.0191 0.6029 0.7524
-1.500 0.0515 0.02378 0.01461 -0.0189 0.5983 0.7541
-1.250 0.0775 0.02369 0.01440 -0.0188 0.5943 0.7560
-1.000 0.1024 0.02358 0.01418 -0.0185 0.5906 0.7583
-0.750 0.1243 0.02345 0.01401 -0.0180 0.5857 0.7612
-0.500 0.1455 0.02325 0.01373 -0.0175 0.5814 0.7642
-0.250 0.1654 0.02295 0.01332 -0.0171 0.5778 0.7683
0.000 0.1918 0.02289 0.01316 -0.0171 0.5749 0.7698
0.250 0.2154 0.02286 0.01315 -0.0167 0.5707 0.7712
0.500 0.2397 0.02284 0.01311 -0.0165 0.5666 0.7730
0.750 0.2646 0.02280 0.01302 -0.0163 0.5630 0.7751
1.000 0.2901 0.02274 0.01288 -0.0163 0.5600 0.7771
1.250 0.3141 0.02270 0.01282 -0.0162 0.5566 0.7791
1.500 0.3368 0.02269 0.01284 -0.0161 0.5528 0.7814
1.750 0.3607 0.02266 0.01278 -0.0162 0.5492 0.7843
2.000 0.3863 0.02267 0.01278 -0.0161 0.5459 0.7859
2.250 0.4132 0.02268 0.01275 -0.0163 0.5432 0.7872
2.500 0.4373 0.02279 0.01291 -0.0161 0.5399 0.7886
2.750 0.4603 0.02292 0.01311 -0.0158 0.5360 0.7903
3.000 0.4848 0.02302 0.01323 -0.0157 0.5324 0.7921
3.250 0.5106 0.02308 0.01330 -0.0158 0.5293 0.7942
3.500 0.5380 0.02314 0.01335 -0.0161 0.5267 0.7964
3.750 0.5616 0.02333 0.01360 -0.0161 0.5231 0.7987
4.000 0.5846 0.02353 0.01389 -0.0161 0.5189 0.8008
4.250 0.6090 0.02368 0.01412 -0.0159 0.5153 0.8022
4.500 0.6350 0.02380 0.01426 -0.0159 0.5123 0.8036
4.750 0.6633 0.02387 0.01434 -0.0163 0.5097 0.8052
5.000 0.6816 0.02425 0.01490 -0.0153 0.5048 0.8073
5.250 0.7038 0.02451 0.01526 -0.0149 0.5005 0.8097
5.500 0.7299 0.02463 0.01544 -0.0150 0.4969 0.8121
5.750 0.7593 0.02468 0.01550 -0.0156 0.4938 0.8143
6.000 0.7779 0.02510 0.01609 -0.0150 0.4884 0.8168
6.250 0.7991 0.02535 0.01647 -0.0143 0.4835 0.8186
6.500 0.8258 0.02538 0.01657 -0.0144 0.4795 0.8204
6.750 0.8505 0.02552 0.01679 -0.0141 0.4753 0.8224
7.000 0.8655 0.02599 0.01746 -0.0128 0.4690 0.8250
7.250 0.8913 0.02604 0.01760 -0.0127 0.4642 0.8277
7.500 0.9194 0.02603 0.01764 -0.0131 0.4598 0.8306
7.750 0.9316 0.02656 0.01838 -0.0114 0.4524 0.8339
8.000 0.9575 0.02646 0.01837 -0.0111 0.4471 0.8363
8.250 0.9740 0.02675 0.01883 -0.0098 0.4406 0.8392
8.500 0.9919 0.02694 0.01916 -0.0086 0.4335 0.8424
8.750 1.0172 0.02685 0.01917 -0.0084 0.4272 0.8455
9.000 1.0266 0.02734 0.01985 -0.0064 0.4187 0.8494
9.250 1.0488 0.02720 0.01981 -0.0055 0.4117 0.8524
9.500 1.0517 0.02773 0.02055 -0.0024 0.4025 0.8570
9.750 1.0620 0.02794 0.02087 -0.0002 0.3941 0.8620
10.000 1.0683 0.02833 0.02141 0.0024 0.3848 0.8675
10.250 1.0653 0.02925 0.02251 0.0057 0.3747 0.8742
10.500 1.0727 0.02982 0.02319 0.0075 0.3642 0.8811
10.750 1.0760 0.03058 0.02406 0.0097 0.3528 0.8885
11.000 1.0693 0.03228 0.02591 0.0117 0.3402 0.8984
11.250 1.0662 0.03395 0.02772 0.0132 0.3269 0.9108
11.750 1.0735 0.03723 0.03117 0.0134 0.2958 0.9877
12.000 1.0763 0.03919 0.03307 0.0134 0.2793 1.0000
12.250 1.0782 0.04133 0.03516 0.0134 0.2630 1.0000
12.750 1.0765 0.04632 0.04003 0.0132 0.2319 1.0000
13.250 1.0707 0.05197 0.04563 0.0127 0.2032 1.0000
13.500 1.0679 0.05493 0.04856 0.0123 0.1900 1.0000
13.750 1.0655 0.05794 0.05157 0.0119 0.1774 1.0000
14.000 1.0635 0.06098 0.05460 0.0113 0.1655 1.0000
14.250 1.0618 0.06406 0.05767 0.0107 0.1545 1.0000
14.500 1.0598 0.06723 0.06078 0.0100 0.1441 1.0000
14.750 1.0580 0.07054 0.06415 0.0091 0.1338 1.0000
15.000 1.0569 0.07382 0.06745 0.0083 0.1244 1.0000
15.250 1.0548 0.07724 0.07085 0.0073 0.1160 1.0000
15.500 1.0533 0.08076 0.07444 0.0062 0.1075 1.0000
15.750 1.0524 0.08420 0.07791 0.0051 0.1001 1.0000
16.000 1.0498 0.08795 0.08166 0.0037 0.0932 1.0000
16.250 1.0490 0.09154 0.08533 0.0025 0.0865 1.0000
16.500 1.0465 0.09538 0.08917 0.0010 0.0809 1.0000
16.750 1.0460 0.09904 0.09292 -0.0004 0.0752 1.0000
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Polar data table (+)
Polar graphs
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