EPPLER 654 AIRFOIL (e654-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 654 AIRFOIL (e654-il) Reynolds number: 200,000 Max Cl/Cd: 71.42 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e654-il-200000-n5.txt Download as CSV file: xf-e654-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 654 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2254 0.05916 0.05414 -0.1343 0.7789 0.0113
-11.500 -0.2706 0.04925 0.04388 -0.1414 0.7749 0.0111
-11.250 -0.2955 0.04415 0.03850 -0.1436 0.7710 0.0111
-11.000 -0.3107 0.04065 0.03479 -0.1441 0.7668 0.0111
-10.750 -0.3238 0.03755 0.03142 -0.1436 0.7626 0.0109
-10.500 -0.3274 0.03561 0.02930 -0.1426 0.7587 0.0111
-10.250 -0.3313 0.03361 0.02706 -0.1411 0.7553 0.0112
-10.000 -0.3335 0.03205 0.02531 -0.1390 0.7519 0.0113
-9.750 -0.3312 0.03059 0.02365 -0.1372 0.7484 0.0115
-9.500 -0.3227 0.02918 0.02203 -0.1358 0.7454 0.0116
-9.250 -0.3115 0.02779 0.02042 -0.1345 0.7426 0.0120
-9.000 -0.2972 0.02656 0.01897 -0.1335 0.7402 0.0123
-8.750 -0.2810 0.02538 0.01756 -0.1326 0.7379 0.0126
-8.500 -0.2636 0.02431 0.01632 -0.1317 0.7356 0.0131
-8.250 -0.2457 0.02349 0.01545 -0.1309 0.7328 0.0134
-8.000 -0.2264 0.02276 0.01466 -0.1302 0.7300 0.0139
-7.750 -0.2061 0.02206 0.01386 -0.1296 0.7274 0.0147
-7.500 -0.1848 0.02140 0.01305 -0.1291 0.7252 0.0158
-7.250 -0.1630 0.02082 0.01245 -0.1287 0.7231 0.0170
-7.000 -0.1402 0.02029 0.01180 -0.1283 0.7213 0.0185
-6.750 -0.1173 0.01971 0.01115 -0.1281 0.7195 0.0201
-6.500 -0.0950 0.01918 0.01056 -0.1276 0.7171 0.0221
-6.250 -0.0722 0.01869 0.01006 -0.1272 0.7145 0.0245
-6.000 -0.0485 0.01824 0.00959 -0.1270 0.7121 0.0287
-5.750 -0.0244 0.01778 0.00910 -0.1267 0.7100 0.0337
-5.500 0.0004 0.01736 0.00866 -0.1266 0.7081 0.0408
-5.250 0.0257 0.01697 0.00829 -0.1266 0.7062 0.0510
-5.000 0.0517 0.01662 0.00794 -0.1267 0.7045 0.0655
-4.750 0.0780 0.01624 0.00761 -0.1269 0.7028 0.0853
-4.500 0.1034 0.01590 0.00737 -0.1270 0.7007 0.1123
-4.250 0.1285 0.01556 0.00718 -0.1270 0.6984 0.1469
-4.000 0.1542 0.01522 0.00701 -0.1272 0.6963 0.1901
-3.750 0.1805 0.01488 0.00684 -0.1276 0.6942 0.2432
-3.500 0.2072 0.01449 0.00669 -0.1280 0.6922 0.3098
-3.250 0.2345 0.01408 0.00655 -0.1285 0.6902 0.3901
-3.000 0.2619 0.01373 0.00649 -0.1288 0.6883 0.4763
-2.750 0.2889 0.01360 0.00661 -0.1287 0.6867 0.5526
-2.500 0.3165 0.01368 0.00676 -0.1285 0.6853 0.6031
-2.250 0.3426 0.01384 0.00695 -0.1282 0.6833 0.6349
-2.000 0.3685 0.01401 0.00713 -0.1278 0.6809 0.6564
-1.750 0.3951 0.01417 0.00725 -0.1276 0.6785 0.6727
-1.500 0.4224 0.01431 0.00735 -0.1275 0.6762 0.6870
-1.250 0.4501 0.01446 0.00744 -0.1275 0.6743 0.7001
-1.000 0.4771 0.01460 0.00756 -0.1272 0.6725 0.7100
-0.750 0.5062 0.01471 0.00758 -0.1276 0.6707 0.7208
-0.500 0.5337 0.01484 0.00767 -0.1274 0.6691 0.7286
-0.250 0.5617 0.01499 0.00777 -0.1276 0.6671 0.7380
0.000 0.5846 0.01519 0.00803 -0.1267 0.6644 0.7439
0.250 0.6101 0.01535 0.00818 -0.1264 0.6616 0.7509
0.500 0.6370 0.01546 0.00827 -0.1264 0.6591 0.7573
0.750 0.6633 0.01556 0.00837 -0.1262 0.6568 0.7622
1.000 0.6917 0.01562 0.00839 -0.1264 0.6548 0.7678
1.250 0.7222 0.01566 0.00837 -0.1271 0.6529 0.7733
1.500 0.7489 0.01575 0.00846 -0.1270 0.6508 0.7768
1.750 0.7706 0.01595 0.00873 -0.1261 0.6471 0.7810
2.000 0.7959 0.01608 0.00887 -0.1259 0.6438 0.7855
2.250 0.8242 0.01615 0.00893 -0.1263 0.6409 0.7901
2.500 0.8515 0.01616 0.00894 -0.1263 0.6383 0.7930
2.750 0.8807 0.01615 0.00891 -0.1267 0.6361 0.7964
3.000 0.9050 0.01629 0.00909 -0.1263 0.6328 0.8003
3.250 0.9277 0.01647 0.00934 -0.1257 0.6285 0.8044
3.500 0.9538 0.01652 0.00941 -0.1257 0.6248 0.8081
3.750 0.9811 0.01650 0.00940 -0.1256 0.6218 0.8111
4.000 1.0111 0.01643 0.00931 -0.1262 0.6192 0.8143
4.250 1.0292 0.01669 0.00969 -0.1248 0.6140 0.8184
4.500 1.0534 0.01678 0.00983 -0.1244 0.6094 0.8227
4.750 1.0801 0.01674 0.00981 -0.1243 0.6057 0.8259
5.000 1.1071 0.01671 0.00980 -0.1243 0.6022 0.8290
5.250 1.1227 0.01697 0.01018 -0.1224 0.5960 0.8333
5.500 1.1470 0.01699 0.01024 -0.1220 0.5910 0.8378
5.750 1.1755 0.01690 0.01016 -0.1223 0.5870 0.8416
6.000 1.1867 0.01720 0.01060 -0.1196 0.5797 0.8460
6.250 1.2097 0.01719 0.01062 -0.1189 0.5741 0.8503
6.500 1.2274 0.01736 0.01088 -0.1174 0.5672 0.8554
6.750 1.2415 0.01746 0.01104 -0.1151 0.5598 0.8605
7.000 1.2562 0.01761 0.01125 -0.1130 0.5524 0.8666
7.250 1.2713 0.01780 0.01149 -0.1110 0.5436 0.8731
7.500 1.2815 0.01811 0.01188 -0.1083 0.5345 0.8797
7.750 1.2993 0.01826 0.01203 -0.1068 0.5250 0.8868
8.000 1.3059 0.01874 0.01259 -0.1037 0.5138 0.8960
8.250 1.3154 0.01919 0.01308 -0.1012 0.5020 0.9076
8.500 1.3246 0.01963 0.01356 -0.0986 0.4894 0.9239
9.000 1.3451 0.02090 0.01481 -0.0948 0.4595 1.0000
9.250 1.3554 0.02186 0.01571 -0.0932 0.4428 1.0000
9.500 1.3636 0.02296 0.01675 -0.0915 0.4257 1.0000
9.750 1.3704 0.02419 0.01793 -0.0898 0.4087 1.0000
10.000 1.3763 0.02554 0.01921 -0.0880 0.3922 1.0000
10.250 1.3812 0.02699 0.02061 -0.0862 0.3762 1.0000
10.500 1.3856 0.02853 0.02211 -0.0845 0.3604 1.0000
10.750 1.3893 0.03015 0.02368 -0.0828 0.3448 1.0000
11.000 1.3932 0.03182 0.02531 -0.0812 0.3300 1.0000
11.250 1.3965 0.03358 0.02704 -0.0797 0.3155 1.0000
11.500 1.3997 0.03540 0.02882 -0.0783 0.3015 1.0000
11.750 1.4033 0.03725 0.03066 -0.0769 0.2878 1.0000
12.000 1.4074 0.03913 0.03253 -0.0758 0.2742 1.0000
12.250 1.4116 0.04106 0.03445 -0.0747 0.2611 1.0000
12.500 1.4157 0.04305 0.03643 -0.0736 0.2485 1.0000
12.750 1.4189 0.04517 0.03853 -0.0727 0.2360 1.0000
13.000 1.4219 0.04735 0.04070 -0.0717 0.2243 1.0000
13.250 1.4262 0.04950 0.04285 -0.0710 0.2124 1.0000
13.500 1.4308 0.05165 0.04501 -0.0703 0.2013 1.0000
13.750 1.4340 0.05400 0.04737 -0.0697 0.1906 1.0000
14.250 1.4409 0.05878 0.05218 -0.0686 0.1700 1.0000
14.500 1.4443 0.06125 0.05467 -0.0682 0.1606 1.0000
15.000 1.4503 0.06644 0.05990 -0.0677 0.1428 1.0000
15.250 1.4523 0.06922 0.06271 -0.0675 0.1350 1.0000
15.500 1.4543 0.07204 0.06556 -0.0674 0.1267 1.0000
15.750 1.4570 0.07484 0.06842 -0.0674 0.1193 1.0000
16.000 1.4570 0.07802 0.07162 -0.0675 0.1123 1.0000
16.250 1.4602 0.08086 0.07453 -0.0676 0.1054 1.0000
16.500 1.4588 0.08431 0.07800 -0.0679 0.0993 1.0000
16.750 1.4619 0.08724 0.08101 -0.0682 0.0932 1.0000
17.000 1.4597 0.09092 0.08473 -0.0687 0.0879 1.0000
17.250 1.4623 0.09399 0.08789 -0.0692 0.0826 1.0000
17.500 1.4599 0.09780 0.09175 -0.0699 0.0779 1.0000
17.750 1.4611 0.10111 0.09516 -0.0706 0.0734 1.0000
18.000 1.4594 0.10489 0.09900 -0.0715 0.0691 1.0000
18.250 1.4583 0.10862 0.10282 -0.0725 0.0654 1.0000
18.500 1.4574 0.11235 0.10663 -0.0736 0.0616 1.0000
18.750 1.4535 0.11658 0.11090 -0.0749 0.0584 1.0000
19.000 1.4538 0.12017 0.11461 -0.0761 0.0550 1.0000
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Polar data table (+)
Polar graphs
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