EPPLER 904 AIRFOIL (e904-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 904 AIRFOIL (e904-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.71 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e904-il-1000000-n5.txt Download as CSV file: xf-e904-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4637 0.12141 0.11970 -0.0282 1.0000 0.0037
-11.000 -0.4618 0.11782 0.11611 -0.0291 1.0000 0.0037
-10.750 -0.4604 0.11404 0.11235 -0.0301 1.0000 0.0037
-4.750 -0.2732 0.01447 0.00928 -0.0580 0.8546 0.0030
-4.500 -0.2498 0.01243 0.00697 -0.0566 0.8525 0.0025
-4.250 -0.2270 0.01090 0.00526 -0.0552 0.8506 0.0021
-4.000 -0.2048 0.00990 0.00412 -0.0539 0.8485 0.0019
-3.750 -0.1821 0.00914 0.00321 -0.0527 0.8465 0.0017
-3.500 -0.1577 0.00865 0.00260 -0.0520 0.8446 0.0016
-3.250 -0.1322 0.00835 0.00221 -0.0515 0.8429 0.0016
-3.000 -0.1061 0.00813 0.00190 -0.0512 0.8412 0.0016
-2.750 -0.0796 0.00799 0.00166 -0.0511 0.8396 0.0016
-2.500 -0.0528 0.00787 0.00148 -0.0510 0.8381 0.0019
-2.250 -0.0259 0.00775 0.00137 -0.0509 0.8367 0.0025
-2.000 0.0009 0.00766 0.00130 -0.0509 0.8349 0.0033
-1.750 0.0224 0.00700 0.00114 -0.0500 0.8324 0.1425
-1.250 0.0573 0.00531 0.00089 -0.0469 0.8275 0.5756
-1.000 0.0804 0.00501 0.00081 -0.0461 0.8246 0.6545
-0.750 0.1028 0.00470 0.00077 -0.0451 0.8206 0.7330
-0.500 0.1254 0.00453 0.00085 -0.0439 0.8158 0.8140
-0.250 0.1513 0.00455 0.00090 -0.0435 0.8110 0.8433
0.000 0.1775 0.00455 0.00093 -0.0432 0.8051 0.8582
0.250 0.2039 0.00458 0.00095 -0.0429 0.7989 0.8678
0.500 0.2304 0.00460 0.00097 -0.0427 0.7919 0.8762
0.750 0.2568 0.00463 0.00101 -0.0424 0.7865 0.8830
1.000 0.2836 0.00465 0.00105 -0.0423 0.7814 0.8898
1.250 0.3102 0.00466 0.00110 -0.0420 0.7758 0.8946
1.500 0.3371 0.00468 0.00114 -0.0420 0.7701 0.8983
1.750 0.3642 0.00470 0.00117 -0.0419 0.7626 0.9009
2.000 0.3914 0.00472 0.00127 -0.0419 0.7537 0.9027
2.250 0.4166 0.00475 0.00129 -0.0414 0.7269 0.9043
2.500 0.4296 0.00525 0.00136 -0.0383 0.6174 0.9067
2.750 0.4384 0.00613 0.00164 -0.0346 0.4657 0.9096
3.000 0.4500 0.00702 0.00193 -0.0317 0.3158 0.9125
3.250 0.4615 0.00805 0.00228 -0.0289 0.1494 0.9151
3.500 0.4744 0.00908 0.00272 -0.0263 0.0059 0.9175
3.750 0.4984 0.00934 0.00299 -0.0257 0.0021 0.9195
4.000 0.5222 0.00961 0.00340 -0.0249 0.0021 0.9215
4.250 0.5461 0.00988 0.00372 -0.0243 0.0018 0.9235
4.500 0.5699 0.01015 0.00403 -0.0237 0.0013 0.9257
4.750 0.5925 0.01057 0.00452 -0.0227 0.0010 0.9280
5.000 0.6132 0.01113 0.00519 -0.0213 0.0009 0.9304
5.250 0.6325 0.01182 0.00600 -0.0196 0.0008 0.9334
5.500 0.6507 0.01271 0.00702 -0.0177 0.0008 0.9369
5.750 0.6690 0.01410 0.00857 -0.0157 0.0008 0.9408
6.000 0.6921 0.01635 0.01105 -0.0143 0.0009 0.9436
6.250 0.7183 0.01945 0.01448 -0.0133 0.0010 0.9460
6.500 0.7388 0.02333 0.01878 -0.0108 0.0013 0.9501
6.750 0.7537 0.02661 0.02242 -0.0079 0.0015 0.9561
7.000 0.7642 0.03035 0.02653 -0.0046 0.0017 0.9644
7.500 0.7691 0.04078 0.03774 0.0017 0.0022 0.9860
7.750 0.7784 0.04472 0.04194 0.0032 0.0022 0.9960
8.000 0.7782 0.04817 0.04561 0.0062 0.0022 1.0000
8.250 0.7739 0.05123 0.04884 0.0099 0.0022 1.0000
8.500 0.7651 0.05445 0.05220 0.0137 0.0022 1.0000
8.750 0.7518 0.05705 0.05491 0.0182 0.0022 1.0000
9.000 0.7371 0.05982 0.05778 0.0219 0.0022 1.0000
9.250 0.7232 0.06282 0.06089 0.0244 0.0022 1.0000
9.500 0.7063 0.06640 0.06456 0.0258 0.0022 1.0000
9.750 0.6919 0.07035 0.06859 0.0258 0.0022 1.0000
10.000 0.6776 0.07512 0.07344 0.0243 0.0022 1.0000
10.250 0.6643 0.08120 0.07959 0.0206 0.0022 1.0000
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Polar data table (+)
Polar graphs
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