EPPLER 642 AIRFOIL (e642-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 642 AIRFOIL (e642-il) Reynolds number: 200,000 Max Cl/Cd: 65.44 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e642-il-200000-n5.txt Download as CSV file: xf-e642-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 642 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.2338 0.11847 0.11447 -0.0590 0.7955 0.0306
-12.750 -0.2315 0.11461 0.11058 -0.0606 0.7915 0.0306
-12.250 -0.2997 0.10920 0.10508 -0.0662 0.8309 0.0193
-12.000 -0.2940 0.10583 0.10163 -0.0678 0.8194 0.0190
-11.750 -0.2933 0.10142 0.09718 -0.0700 0.8104 0.0189
-11.500 -0.2956 0.09641 0.09214 -0.0724 0.8032 0.0190
-11.250 -0.2982 0.09157 0.08729 -0.0748 0.7965 0.0189
-11.000 -0.3048 0.08580 0.08150 -0.0777 0.7907 0.0190
-10.750 -0.3086 0.08107 0.07676 -0.0802 0.7852 0.0185
-10.500 -0.3206 0.07391 0.06961 -0.0848 0.7799 0.0184
-10.250 -0.3460 0.06444 0.06006 -0.0918 0.7750 0.0177
-10.000 -0.3732 0.05830 0.05376 -0.0938 0.7701 0.0176
-9.750 -0.4024 0.05306 0.04831 -0.0928 0.7651 0.0171
-9.500 -0.4242 0.04926 0.04428 -0.0901 0.7607 0.0169
-9.250 -0.4485 0.04548 0.04018 -0.0857 0.7572 0.0166
-9.000 -0.4713 0.04039 0.03457 -0.0809 0.7534 0.0161
-8.750 -0.4786 0.03665 0.03029 -0.0771 0.7499 0.0158
-8.500 -0.4734 0.03416 0.02743 -0.0746 0.7468 0.0158
-8.250 -0.4634 0.03201 0.02491 -0.0726 0.7440 0.0158
-8.000 -0.4498 0.03009 0.02265 -0.0709 0.7416 0.0159
-7.750 -0.4331 0.02837 0.02067 -0.0696 0.7386 0.0160
-7.500 -0.4141 0.02686 0.01891 -0.0686 0.7355 0.0162
-7.250 -0.3934 0.02552 0.01736 -0.0677 0.7327 0.0164
-7.000 -0.3710 0.02430 0.01593 -0.0671 0.7304 0.0167
-6.750 -0.3475 0.02316 0.01461 -0.0665 0.7283 0.0170
-6.500 -0.3233 0.02218 0.01346 -0.0661 0.7264 0.0173
-6.250 -0.2990 0.02131 0.01247 -0.0657 0.7243 0.0179
-6.000 -0.2746 0.02058 0.01164 -0.0652 0.7219 0.0188
-5.750 -0.2503 0.01994 0.01089 -0.0648 0.7194 0.0196
-5.500 -0.2276 0.01909 0.01002 -0.0641 0.7170 0.0202
-5.250 -0.2051 0.01845 0.00933 -0.0634 0.7148 0.0207
-5.000 -0.1824 0.01792 0.00875 -0.0627 0.7129 0.0214
-4.750 -0.1594 0.01746 0.00822 -0.0620 0.7113 0.0221
-4.500 -0.1362 0.01704 0.00773 -0.0613 0.7095 0.0233
-4.250 -0.1129 0.01668 0.00730 -0.0606 0.7071 0.0245
-4.000 -0.0898 0.01630 0.00692 -0.0599 0.7047 0.0267
-3.750 -0.0660 0.01601 0.00661 -0.0594 0.7025 0.0312
-3.500 -0.0431 0.01562 0.00628 -0.0587 0.7004 0.0441
-3.250 -0.0214 0.01512 0.00598 -0.0578 0.6984 0.0887
-2.750 0.0166 0.01385 0.00552 -0.0555 0.6947 0.2908
-2.500 0.0258 0.01278 0.00534 -0.0527 0.6925 0.4942
-2.250 0.0485 0.01309 0.00687 -0.0490 0.6902 0.7607
-2.000 0.0646 0.01335 0.00705 -0.0466 0.6877 0.8084
-1.750 0.0863 0.01371 0.00731 -0.0450 0.6854 0.8300
-1.500 0.1106 0.01400 0.00750 -0.0439 0.6832 0.8433
-1.250 0.1383 0.01445 0.00788 -0.0429 0.6812 0.8568
-1.000 0.1698 0.01489 0.00822 -0.0426 0.6795 0.8687
-0.750 0.1971 0.01511 0.00839 -0.0422 0.6772 0.8776
-0.500 0.2260 0.01527 0.00851 -0.0422 0.6744 0.8837
-0.250 0.2469 0.01530 0.00851 -0.0409 0.6716 0.8902
0.000 0.2781 0.01535 0.00850 -0.0416 0.6691 0.8930
0.250 0.3074 0.01537 0.00845 -0.0420 0.6667 0.8961
0.500 0.3325 0.01536 0.00837 -0.0416 0.6646 0.9000
0.750 0.3522 0.01534 0.00830 -0.0402 0.6624 0.9042
1.000 0.3787 0.01537 0.00834 -0.0402 0.6590 0.9059
1.250 0.4051 0.01537 0.00835 -0.0402 0.6557 0.9078
1.500 0.4314 0.01536 0.00831 -0.0401 0.6527 0.9097
1.750 0.4574 0.01532 0.00823 -0.0399 0.6501 0.9117
2.000 0.4830 0.01527 0.00814 -0.0397 0.6477 0.9136
2.250 0.4999 0.01529 0.00820 -0.0379 0.6436 0.9165
2.500 0.5196 0.01528 0.00821 -0.0367 0.6397 0.9186
2.750 0.5465 0.01523 0.00816 -0.0367 0.6362 0.9196
3.000 0.5748 0.01517 0.00807 -0.0370 0.6332 0.9207
3.250 0.5984 0.01517 0.00811 -0.0365 0.6289 0.9219
3.500 0.6209 0.01516 0.00816 -0.0358 0.6240 0.9233
3.750 0.6465 0.01510 0.00811 -0.0355 0.6198 0.9247
4.000 0.6731 0.01501 0.00801 -0.0355 0.6162 0.9259
4.250 0.6914 0.01504 0.00813 -0.0340 0.6099 0.9276
4.500 0.7153 0.01496 0.00809 -0.0335 0.6047 0.9288
4.750 0.7389 0.01489 0.00804 -0.0329 0.5998 0.9302
5.000 0.7579 0.01489 0.00813 -0.0316 0.5927 0.9322
5.250 0.7842 0.01477 0.00801 -0.0314 0.5872 0.9330
5.500 0.8046 0.01479 0.00815 -0.0304 0.5786 0.9341
5.750 0.8299 0.01469 0.00807 -0.0301 0.5714 0.9351
6.000 0.8505 0.01470 0.00818 -0.0290 0.5615 0.9364
6.250 0.8721 0.01469 0.00823 -0.0281 0.5515 0.9377
6.500 0.8942 0.01465 0.00824 -0.0273 0.5412 0.9392
6.750 0.9150 0.01464 0.00825 -0.0262 0.5290 0.9411
7.000 0.9345 0.01468 0.00831 -0.0249 0.5150 0.9428
7.250 0.9535 0.01475 0.00838 -0.0236 0.4998 0.9445
7.500 0.9708 0.01488 0.00850 -0.0220 0.4831 0.9463
7.750 0.9869 0.01508 0.00868 -0.0202 0.4644 0.9481
8.000 1.0003 0.01533 0.00891 -0.0180 0.4457 0.9503
8.250 1.0115 0.01570 0.00925 -0.0156 0.4261 0.9531
8.500 1.0220 0.01618 0.00969 -0.0132 0.4053 0.9564
8.750 1.0316 0.01675 0.01023 -0.0109 0.3846 0.9601
9.000 1.0420 0.01748 0.01092 -0.0091 0.3625 0.9641
9.250 1.0514 0.01837 0.01176 -0.0075 0.3389 0.9687
9.500 1.0603 0.01946 0.01281 -0.0062 0.3146 0.9739
9.750 1.0688 0.02081 0.01407 -0.0055 0.2882 0.9809
10.000 1.0763 0.02220 0.01539 -0.0048 0.2629 1.0000
10.250 1.0780 0.02371 0.01679 -0.0031 0.2391 1.0000
10.500 1.0809 0.02528 0.01828 -0.0017 0.2172 1.0000
10.750 1.0861 0.02680 0.01973 -0.0005 0.1976 1.0000
11.000 1.0910 0.02839 0.02126 0.0005 0.1781 1.0000
11.250 1.0946 0.03012 0.02291 0.0015 0.1590 1.0000
11.500 1.1008 0.03171 0.02445 0.0023 0.1425 1.0000
11.750 1.1057 0.03344 0.02612 0.0032 0.1244 1.0000
12.000 1.1107 0.03518 0.02781 0.0039 0.1086 1.0000
12.250 1.1152 0.03701 0.02958 0.0047 0.0935 1.0000
12.500 1.1195 0.03892 0.03144 0.0053 0.0795 1.0000
12.750 1.1239 0.04086 0.03335 0.0059 0.0664 1.0000
13.000 1.1276 0.04292 0.03538 0.0064 0.0540 1.0000
13.250 1.1311 0.04505 0.03750 0.0069 0.0441 1.0000
13.500 1.1332 0.04738 0.03981 0.0073 0.0345 1.0000
13.750 1.1359 0.04973 0.04217 0.0076 0.0280 1.0000
14.000 1.1364 0.05238 0.04483 0.0079 0.0217 1.0000
14.250 1.1386 0.05493 0.04744 0.0080 0.0191 1.0000
14.500 1.1417 0.05746 0.05006 0.0080 0.0174 1.0000
14.750 1.1439 0.06014 0.05283 0.0078 0.0164 1.0000
15.000 1.1435 0.06322 0.05601 0.0076 0.0153 1.0000
15.250 1.1453 0.06613 0.05904 0.0072 0.0146 1.0000
15.500 1.1453 0.06932 0.06236 0.0067 0.0140 1.0000
15.750 1.1444 0.07271 0.06587 0.0061 0.0134 1.0000
16.000 1.1431 0.07625 0.06953 0.0053 0.0131 1.0000
16.250 1.1406 0.08003 0.07342 0.0043 0.0127 1.0000
16.500 1.1357 0.08425 0.07774 0.0030 0.0123 1.0000
16.750 1.1328 0.08826 0.08188 0.0018 0.0121 1.0000
17.000 1.1298 0.09237 0.08612 0.0004 0.0119 1.0000
17.250 1.1271 0.09650 0.09038 -0.0011 0.0117 1.0000
17.500 1.1241 0.10076 0.09478 -0.0027 0.0113 1.0000
17.750 1.1204 0.10515 0.09930 -0.0045 0.0113 1.0000
18.000 1.1177 0.10947 0.10375 -0.0064 0.0109 1.0000
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Polar data table (+)
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