EPPLER 548 AIRFOIL (e548-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 548 AIRFOIL (e548-il) Reynolds number: 200,000 Max Cl/Cd: 63.42 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e548-il-200000-n5.txt Download as CSV file: xf-e548-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.6139 0.07247 0.06827 -0.0571 1.0000 0.0082
-13.000 -0.6534 0.06389 0.05931 -0.0603 1.0000 0.0080
-12.750 -0.6752 0.05875 0.05393 -0.0611 1.0000 0.0080
-12.500 -0.6892 0.05496 0.04997 -0.0610 1.0000 0.0080
-12.250 -0.7040 0.05117 0.04592 -0.0603 1.0000 0.0080
-12.000 -0.7109 0.04852 0.04315 -0.0594 1.0000 0.0081
-11.750 -0.7203 0.04545 0.03983 -0.0578 1.0000 0.0080
-11.500 -0.7218 0.04360 0.03792 -0.0564 1.0000 0.0083
-11.250 -0.7251 0.04121 0.03531 -0.0545 1.0000 0.0083
-11.000 -0.7247 0.03936 0.03332 -0.0526 1.0000 0.0084
-10.750 -0.7231 0.03758 0.03139 -0.0505 1.0000 0.0085
-10.500 -0.7189 0.03579 0.02941 -0.0484 1.0000 0.0085
-10.250 -0.7137 0.03431 0.02779 -0.0463 1.0000 0.0088
-10.000 -0.7004 0.03263 0.02595 -0.0452 0.9931 0.0089
-9.750 -0.6651 0.03050 0.02357 -0.0481 0.9470 0.0093
-9.500 -0.6061 0.02833 0.02100 -0.0553 0.9095 0.0102
-9.250 -0.5504 0.02674 0.01920 -0.0623 0.8648 0.0110
-8.750 -0.4895 0.02479 0.01673 -0.0651 0.7974 0.0129
-8.500 -0.4714 0.02396 0.01578 -0.0643 0.7743 0.0133
-8.250 -0.4554 0.02323 0.01493 -0.0630 0.7548 0.0137
-8.000 -0.4401 0.02250 0.01408 -0.0615 0.7377 0.0146
-7.750 -0.4257 0.02179 0.01320 -0.0598 0.7223 0.0157
-7.500 -0.4122 0.02108 0.01240 -0.0581 0.7085 0.0170
-7.250 -0.3975 0.02050 0.01172 -0.0564 0.6953 0.0186
-7.000 -0.3838 0.01989 0.01103 -0.0546 0.6837 0.0205
-6.750 -0.3704 0.01932 0.01038 -0.0527 0.6736 0.0237
-6.500 -0.3583 0.01875 0.00975 -0.0505 0.6638 0.0277
-6.250 -0.3475 0.01826 0.00921 -0.0480 0.6552 0.0333
-6.000 -0.3358 0.01773 0.00870 -0.0457 0.6467 0.0437
-5.750 -0.3228 0.01719 0.00819 -0.0436 0.6392 0.0607
-5.500 -0.3092 0.01664 0.00773 -0.0416 0.6313 0.0862
-5.000 -0.2872 0.01518 0.00674 -0.0371 0.6174 0.1947
-4.750 -0.2827 0.01400 0.00609 -0.0341 0.6112 0.3102
-4.500 -0.2823 0.01261 0.00569 -0.0300 0.6060 0.5045
-4.250 -0.2586 0.01308 0.00651 -0.0283 0.5999 0.6126
-4.000 -0.2329 0.01325 0.00650 -0.0278 0.5944 0.6391
-3.750 -0.2062 0.01358 0.00670 -0.0273 0.5893 0.6565
-3.500 -0.1793 0.01403 0.00707 -0.0266 0.5837 0.6726
-3.250 -0.1526 0.01462 0.00756 -0.0257 0.5785 0.6879
-3.000 -0.1255 0.01531 0.00817 -0.0246 0.5739 0.7013
-2.750 -0.0974 0.01571 0.00853 -0.0240 0.5688 0.7068
-2.500 -0.0701 0.01572 0.00844 -0.0239 0.5644 0.7092
-2.250 -0.0432 0.01567 0.00825 -0.0239 0.5605 0.7117
-2.000 -0.0163 0.01556 0.00802 -0.0241 0.5569 0.7142
-1.750 0.0105 0.01540 0.00776 -0.0243 0.5526 0.7170
-1.500 0.0375 0.01525 0.00749 -0.0246 0.5485 0.7194
-1.250 0.0650 0.01524 0.00738 -0.0247 0.5448 0.7205
-1.000 0.0926 0.01523 0.00728 -0.0248 0.5416 0.7217
-0.750 0.1202 0.01519 0.00720 -0.0249 0.5380 0.7228
-0.500 0.1477 0.01517 0.00714 -0.0251 0.5345 0.7241
-0.250 0.1753 0.01515 0.00707 -0.0252 0.5313 0.7257
0.000 0.2030 0.01514 0.00698 -0.0255 0.5282 0.7272
0.250 0.2309 0.01514 0.00688 -0.0258 0.5254 0.7286
0.500 0.2585 0.01510 0.00683 -0.0260 0.5219 0.7301
0.750 0.2863 0.01508 0.00678 -0.0264 0.5187 0.7318
1.000 0.3143 0.01507 0.00673 -0.0268 0.5158 0.7338
1.250 0.3425 0.01506 0.00666 -0.0272 0.5130 0.7355
1.500 0.3704 0.01510 0.00664 -0.0275 0.5104 0.7364
1.750 0.3979 0.01514 0.00669 -0.0276 0.5076 0.7373
2.000 0.4253 0.01518 0.00676 -0.0278 0.5045 0.7383
2.250 0.4528 0.01523 0.00683 -0.0280 0.5016 0.7394
2.500 0.4803 0.01528 0.00690 -0.0282 0.4987 0.7406
2.750 0.5080 0.01535 0.00695 -0.0284 0.4960 0.7420
3.000 0.5360 0.01544 0.00701 -0.0287 0.4937 0.7436
3.250 0.5633 0.01552 0.00715 -0.0289 0.4909 0.7451
3.500 0.5905 0.01560 0.00727 -0.0291 0.4877 0.7466
3.750 0.6179 0.01567 0.00737 -0.0293 0.4845 0.7481
4.000 0.6456 0.01575 0.00747 -0.0296 0.4816 0.7496
4.250 0.6736 0.01584 0.00754 -0.0300 0.4789 0.7511
4.500 0.7014 0.01595 0.00766 -0.0303 0.4761 0.7524
4.750 0.7272 0.01605 0.00788 -0.0302 0.4724 0.7535
5.000 0.7533 0.01615 0.00806 -0.0302 0.4686 0.7548
5.250 0.7798 0.01624 0.00820 -0.0302 0.4649 0.7562
5.500 0.8070 0.01634 0.00832 -0.0303 0.4616 0.7579
5.750 0.8323 0.01646 0.00855 -0.0301 0.4574 0.7596
6.000 0.8578 0.01657 0.00877 -0.0300 0.4528 0.7612
6.250 0.8839 0.01666 0.00891 -0.0300 0.4486 0.7629
6.500 0.9110 0.01676 0.00900 -0.0301 0.4446 0.7646
6.750 0.9349 0.01688 0.00929 -0.0298 0.4388 0.7665
7.000 0.9601 0.01697 0.00945 -0.0297 0.4334 0.7683
7.250 0.9855 0.01705 0.00956 -0.0295 0.4286 0.7697
7.500 1.0078 0.01718 0.00988 -0.0288 0.4219 0.7713
7.750 1.0315 0.01727 0.01004 -0.0283 0.4156 0.7730
8.000 1.0540 0.01740 0.01030 -0.0277 0.4086 0.7751
8.250 1.0762 0.01752 0.01052 -0.0269 0.4006 0.7774
8.500 1.0977 0.01767 0.01078 -0.0262 0.3919 0.7799
8.750 1.1185 0.01781 0.01096 -0.0253 0.3826 0.7823
9.000 1.1382 0.01801 0.01128 -0.0243 0.3711 0.7847
9.250 1.1555 0.01822 0.01160 -0.0228 0.3584 0.7867
9.500 1.1706 0.01849 0.01192 -0.0210 0.3437 0.7889
9.750 1.1821 0.01885 0.01230 -0.0186 0.3266 0.7916
10.000 1.1872 0.01931 0.01274 -0.0153 0.3086 0.7946
10.250 1.1902 0.02000 0.01340 -0.0119 0.2892 0.7980
10.500 1.1906 0.02091 0.01427 -0.0085 0.2694 0.8015
10.750 1.1881 0.02199 0.01535 -0.0051 0.2519 0.8048
11.000 1.1834 0.02336 0.01670 -0.0019 0.2350 0.8090
11.250 1.1784 0.02497 0.01830 0.0007 0.2195 0.8137
11.500 1.1738 0.02679 0.02013 0.0029 0.2050 0.8184
11.750 1.1689 0.02878 0.02215 0.0047 0.1916 0.8229
12.000 1.1642 0.03100 0.02440 0.0060 0.1786 0.8281
12.500 1.1544 0.03591 0.02935 0.0079 0.1552 0.8390
12.750 1.1492 0.03856 0.03202 0.0085 0.1447 0.8457
13.000 1.1461 0.04110 0.03462 0.0090 0.1340 0.8528
13.250 1.1430 0.04369 0.03727 0.0093 0.1247 0.8617
13.500 1.1382 0.04651 0.04014 0.0096 0.1160 0.8723
13.750 1.1363 0.04913 0.04285 0.0097 0.1074 0.8878
14.000 1.1358 0.05190 0.04573 0.0092 0.0993 0.9168
14.500 1.1331 0.05770 0.05162 0.0080 0.0845 1.0000
14.750 1.1316 0.06083 0.05477 0.0074 0.0783 1.0000
15.000 1.1317 0.06386 0.05782 0.0066 0.0720 1.0000
15.250 1.1309 0.06704 0.06103 0.0058 0.0665 1.0000
15.500 1.1299 0.07031 0.06433 0.0050 0.0611 1.0000
15.750 1.1297 0.07352 0.06759 0.0041 0.0564 1.0000
16.000 1.1282 0.07699 0.07109 0.0030 0.0519 1.0000
16.250 1.1278 0.08036 0.07451 0.0019 0.0480 1.0000
16.500 1.1264 0.08394 0.07815 0.0007 0.0443 1.0000
16.750 1.1248 0.08761 0.08187 -0.0006 0.0414 1.0000
17.000 1.1242 0.09120 0.08554 -0.0019 0.0383 1.0000
17.250 1.1203 0.09532 0.08969 -0.0035 0.0360 1.0000
17.500 1.1204 0.09891 0.09339 -0.0049 0.0336 1.0000
17.750 1.1180 0.10295 0.09750 -0.0066 0.0314 1.0000
18.000 1.1144 0.10723 0.10182 -0.0085 0.0296 1.0000
18.250 1.1136 0.11111 0.10582 -0.0102 0.0277 1.0000
18.500 1.1099 0.11551 0.11029 -0.0123 0.0261 1.0000
18.750 1.1058 0.12001 0.11485 -0.0145 0.0249 1.0000
19.000 1.1045 0.12412 0.11909 -0.0165 0.0233 1.0000
19.250 1.1016 0.12854 0.12360 -0.0188 0.0221 1.0000
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Polar data table (+)
Polar graphs
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