EPPLER 904 AIRFOIL (e904-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 904 AIRFOIL (e904-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.93 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e904-il-1000000.txt Download as CSV file: xf-e904-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4841 0.08883 0.08727 -0.0362 1.0000 0.0041
-9.000 -0.4889 0.08514 0.08361 -0.0371 1.0000 0.0041
-8.750 -0.4977 0.08132 0.07983 -0.0379 1.0000 0.0042
-8.500 -0.4947 0.07443 0.07296 -0.0469 0.9980 0.0041
-8.250 -0.4895 0.06707 0.06554 -0.0574 0.9935 0.0041
-8.000 -0.4818 0.06078 0.05915 -0.0633 0.9867 0.0042
-7.750 -0.4696 0.05411 0.05233 -0.0687 0.9827 0.0042
-7.500 -0.4611 0.04919 0.04727 -0.0702 0.9723 0.0043
-7.250 -0.4476 0.04396 0.04183 -0.0717 0.9634 0.0045
-7.000 -0.4297 0.03884 0.03647 -0.0731 0.9563 0.0047
-6.750 -0.4120 0.03441 0.03176 -0.0733 0.9469 0.0050
-6.500 -0.3946 0.03070 0.02776 -0.0724 0.9372 0.0054
-6.250 -0.3745 0.02839 0.02521 -0.0713 0.9292 0.0060
-6.000 -0.3506 0.02762 0.02426 -0.0702 0.9225 0.0067
-5.750 -0.3349 0.02545 0.02177 -0.0682 0.9159 0.0068
-5.500 -0.3195 0.02320 0.01922 -0.0661 0.9097 0.0068
-5.250 -0.3017 0.02102 0.01673 -0.0643 0.9049 0.0068
-4.750 -0.2671 0.01322 0.00811 -0.0596 0.8969 0.0049
-4.500 -0.2451 0.01087 0.00544 -0.0576 0.8939 0.0038
-4.250 -0.2227 0.00991 0.00433 -0.0564 0.8911 0.0040
-4.000 -0.1992 0.00935 0.00371 -0.0556 0.8885 0.0049
-3.750 -0.1744 0.00899 0.00330 -0.0550 0.8860 0.0061
-3.500 -0.1490 0.00872 0.00297 -0.0546 0.8835 0.0067
-3.250 -0.1248 0.00826 0.00239 -0.0539 0.8813 0.0085
-3.000 -0.0987 0.00800 0.00199 -0.0535 0.8794 0.0109
-2.750 -0.0809 0.00699 0.00169 -0.0520 0.8770 0.1956
-2.500 -0.0704 0.00565 0.00147 -0.0493 0.8739 0.5090
-2.250 -0.0559 0.00486 0.00133 -0.0468 0.8710 0.7000
-2.000 -0.0353 0.00459 0.00141 -0.0451 0.8688 0.8101
-1.750 -0.0089 0.00463 0.00144 -0.0448 0.8670 0.8390
-1.500 0.0186 0.00468 0.00146 -0.0448 0.8649 0.8519
-1.250 0.0453 0.00471 0.00147 -0.0446 0.8626 0.8615
-1.000 0.0722 0.00473 0.00147 -0.0444 0.8596 0.8692
-0.750 0.0990 0.00475 0.00146 -0.0442 0.8562 0.8772
-0.500 0.1262 0.00479 0.00148 -0.0441 0.8526 0.8833
-0.250 0.1516 0.00484 0.00154 -0.0435 0.8484 0.8932
0.000 0.1769 0.00488 0.00158 -0.0428 0.8435 0.9023
0.250 0.2031 0.00493 0.00162 -0.0423 0.8387 0.9088
0.500 0.2279 0.00496 0.00166 -0.0416 0.8336 0.9156
0.750 0.2537 0.00497 0.00170 -0.0411 0.8293 0.9207
1.000 0.2798 0.00503 0.00176 -0.0407 0.8260 0.9262
1.250 0.3052 0.00504 0.00180 -0.0402 0.8221 0.9306
1.500 0.3314 0.00505 0.00184 -0.0398 0.8176 0.9337
1.750 0.3585 0.00507 0.00191 -0.0397 0.8139 0.9363
2.000 0.3851 0.00508 0.00195 -0.0395 0.8093 0.9387
2.250 0.4109 0.00505 0.00195 -0.0392 0.8016 0.9409
2.500 0.4355 0.00501 0.00191 -0.0385 0.7866 0.9429
2.750 0.4469 0.00516 0.00171 -0.0346 0.6740 0.9459
3.000 0.4465 0.00621 0.00197 -0.0288 0.4837 0.9506
3.250 0.4346 0.00825 0.00249 -0.0215 0.1238 0.9571
3.500 0.4492 0.00915 0.00298 -0.0189 0.0068 0.9605
3.750 0.4733 0.00943 0.00340 -0.0182 0.0062 0.9629
4.000 0.4963 0.00980 0.00386 -0.0172 0.0062 0.9658
4.500 0.5409 0.01089 0.00518 -0.0149 0.0071 0.9718
4.750 0.5639 0.01162 0.00599 -0.0141 0.0070 0.9746
5.000 0.5852 0.01274 0.00715 -0.0132 0.0055 0.9778
5.250 0.6096 0.01365 0.00813 -0.0126 0.0056 0.9808
5.500 0.6358 0.01537 0.00999 -0.0124 0.0044 0.9826
5.750 0.6665 0.01656 0.01133 -0.0129 0.0036 0.9835
7.750 0.7832 0.02983 0.02711 0.0014 0.0034 1.0000
8.000 0.7805 0.03304 0.03049 0.0055 0.0033 1.0000
8.250 0.7773 0.03678 0.03441 0.0090 0.0032 1.0000
8.500 0.7707 0.04057 0.03836 0.0125 0.0031 1.0000
8.750 0.7594 0.04385 0.04177 0.0164 0.0030 1.0000
9.000 0.7427 0.04690 0.04493 0.0205 0.0030 1.0000
9.250 0.7231 0.05028 0.04843 0.0236 0.0031 1.0000
9.500 0.7017 0.05409 0.05234 0.0255 0.0031 1.0000
9.750 0.6792 0.05855 0.05690 0.0260 0.0032 1.0000
10.000 0.6540 0.06422 0.06266 0.0248 0.0033 1.0000
10.250 0.6289 0.07132 0.06985 0.0211 0.0035 1.0000
10.500 0.6053 0.08193 0.08051 0.0133 0.0038 1.0000
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Polar data table (+)
Polar graphs
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