EPPLER 904 AIRFOIL (e904-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 904 AIRFOIL (e904-il) Reynolds number: 200,000 Max Cl/Cd: 61.53 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e904-il-200000.txt Download as CSV file: xf-e904-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 904 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4760 0.09105 0.08764 -0.0389 1.0000 0.0313
-8.750 -0.4817 0.08745 0.08410 -0.0397 1.0000 0.0320
-8.500 -0.4899 0.08397 0.08069 -0.0406 1.0000 0.0325
-8.250 -0.5043 0.08066 0.07746 -0.0412 1.0000 0.0325
-8.000 -0.5278 0.07853 0.07540 -0.0390 1.0000 0.0320
-7.750 -0.5578 0.07734 0.07427 -0.0338 1.0000 0.0316
-7.500 -0.5772 0.07540 0.07233 -0.0305 1.0000 0.0314
-7.250 -0.5930 0.07288 0.06980 -0.0277 1.0000 0.0317
-7.000 -0.6046 0.07012 0.06699 -0.0253 1.0000 0.0322
-6.750 -0.6127 0.06714 0.06394 -0.0232 1.0000 0.0328
-6.500 -0.6180 0.06389 0.06058 -0.0212 1.0000 0.0341
-6.250 -0.6194 0.06065 0.05719 -0.0193 1.0000 0.0356
-6.000 -0.6000 0.05853 0.05436 -0.0198 0.9967 0.0387
-5.750 -0.5956 0.05064 0.04648 -0.0207 0.9947 0.0405
-5.500 -0.5810 0.04757 0.04336 -0.0205 0.9925 0.0427
-5.250 -0.5651 0.04462 0.04018 -0.0200 0.9899 0.0465
-5.000 -0.5485 0.04077 0.03583 -0.0193 0.9870 0.0536
-4.750 -0.5281 0.03823 0.03319 -0.0192 0.9851 0.0579
-4.500 -0.5058 0.03535 0.02992 -0.0191 0.9831 0.0677
-4.250 -0.4714 0.02817 0.02165 -0.0153 0.9822 0.0236
-4.000 -0.4487 0.02479 0.01769 -0.0132 0.9806 0.0192
-3.750 -0.4223 0.02256 0.01497 -0.0117 0.9789 0.0171
-3.500 -0.3962 0.02080 0.01298 -0.0110 0.9771 0.0180
-3.250 -0.3691 0.02009 0.01211 -0.0110 0.9748 0.0248
-3.000 -0.3415 0.01885 0.01076 -0.0107 0.9730 0.0248
-2.750 -0.3127 0.01785 0.00965 -0.0107 0.9712 0.0262
-2.500 -0.2832 0.01700 0.00865 -0.0110 0.9694 0.0326
-2.250 -0.2776 0.01436 0.00797 -0.0076 0.9660 0.4265
-2.000 -0.2774 0.01349 0.00895 0.0005 0.9629 0.8984
-1.750 -0.1512 0.01521 0.01018 -0.0172 0.9710 0.9718
-1.500 -0.0832 0.01549 0.01021 -0.0257 0.9724 0.9845
-1.250 0.0015 0.01562 0.01013 -0.0380 0.9765 1.0000
-1.000 0.0305 0.01565 0.01007 -0.0390 0.9731 1.0000
-0.750 0.0641 0.01573 0.01003 -0.0410 0.9705 1.0000
-0.500 0.0861 0.01572 0.00997 -0.0405 0.9657 1.0000
-0.250 0.1133 0.01575 0.00995 -0.0411 0.9614 1.0000
0.000 0.1482 0.01582 0.00998 -0.0433 0.9583 1.0000
0.250 0.1729 0.01586 0.01001 -0.0433 0.9533 1.0000
0.500 0.2025 0.01587 0.01002 -0.0442 0.9482 1.0000
0.750 0.2439 0.01588 0.01003 -0.0475 0.9450 1.0000
1.000 0.2668 0.01588 0.01005 -0.0470 0.9378 1.0000
1.250 0.3093 0.01578 0.01001 -0.0502 0.9333 1.0000
1.500 0.3463 0.01567 0.00996 -0.0523 0.9268 1.0000
1.750 0.3962 0.01534 0.00981 -0.0568 0.9207 1.0000
2.000 0.4626 0.01481 0.00944 -0.0644 0.9181 1.0000
2.250 0.4869 0.01473 0.00948 -0.0638 0.9092 1.0000
2.500 0.5449 0.01422 0.00920 -0.0698 0.9063 1.0000
2.750 0.6264 0.01018 0.00510 -0.0728 0.7721 1.0000
3.000 0.6137 0.01150 0.00469 -0.0634 0.4267 1.0000
3.250 0.5916 0.01474 0.00580 -0.0545 0.0298 1.0000
3.500 0.6050 0.01555 0.00678 -0.0514 0.0227 1.0000
3.750 0.6176 0.01633 0.00771 -0.0483 0.0217 1.0000
4.000 0.6295 0.01720 0.00867 -0.0451 0.0210 1.0000
4.250 0.6420 0.01829 0.00983 -0.0419 0.0208 1.0000
4.500 0.6587 0.01969 0.01126 -0.0395 0.0211 1.0000
4.750 0.6834 0.02174 0.01338 -0.0385 0.0217 1.0000
5.000 0.7085 0.02319 0.01493 -0.0374 0.0231 1.0000
5.250 0.7377 0.02507 0.01725 -0.0358 0.0288 1.0000
7.000 0.8139 0.04435 0.03893 -0.0093 0.0435 1.0000
7.250 0.8149 0.04601 0.04089 -0.0047 0.0398 1.0000
7.500 0.8173 0.04845 0.04347 -0.0012 0.0374 1.0000
7.750 0.8217 0.05160 0.04666 0.0012 0.0358 1.0000
8.500 0.7995 0.06246 0.05819 0.0121 0.0327 1.0000
8.750 0.7899 0.06439 0.06041 0.0161 0.0313 1.0000
9.000 0.7763 0.06712 0.06330 0.0197 0.0305 1.0000
9.250 0.7598 0.07013 0.06643 0.0225 0.0302 1.0000
9.500 0.7430 0.07357 0.06997 0.0240 0.0301 1.0000
9.750 0.7262 0.07758 0.07406 0.0240 0.0303 1.0000
10.000 0.7085 0.08251 0.07907 0.0223 0.0303 1.0000
10.250 0.6936 0.08839 0.08499 0.0188 0.0306 1.0000
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Polar data table (+)
Polar graphs
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