EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 297 AIRFOIL (e297-il) Reynolds number: 1,000,000 Max Cl/Cd: 60.44 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e297-il-1000000-n5.txt Download as CSV file: xf-e297-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 297 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8422 0.10314 0.10141 -0.0030 1.0000 0.0016
-14.500 -0.8745 0.08990 0.08807 -0.0101 1.0000 0.0015
-14.250 -0.8985 0.07884 0.07687 -0.0170 1.0000 0.0015
-14.000 -0.9235 0.06857 0.06644 -0.0239 1.0000 0.0015
-13.750 -0.9482 0.05993 0.05762 -0.0294 1.0000 0.0015
-13.500 -0.9676 0.05348 0.05099 -0.0329 1.0000 0.0015
-13.250 -0.9767 0.04925 0.04665 -0.0346 1.0000 0.0015
-13.000 -0.9924 0.04469 0.04190 -0.0355 1.0000 0.0015
-12.750 -1.0051 0.04089 0.03793 -0.0355 1.0000 0.0015
-12.500 -1.0186 0.03734 0.03417 -0.0346 1.0000 0.0015
-12.250 -1.0245 0.03474 0.03140 -0.0332 1.0000 0.0015
-12.000 -1.0306 0.03223 0.02871 -0.0314 1.0000 0.0015
-11.750 -1.0355 0.02991 0.02619 -0.0291 1.0000 0.0015
-11.500 -1.0353 0.02813 0.02425 -0.0268 1.0000 0.0015
-11.250 -1.0338 0.02649 0.02244 -0.0243 1.0000 0.0015
-11.000 -1.0334 0.02477 0.02051 -0.0212 1.0000 0.0015
-10.750 -1.0274 0.02345 0.01904 -0.0185 0.9836 0.0015
-10.500 -1.0075 0.02198 0.01732 -0.0186 0.9343 0.0015
-10.250 -0.9965 0.02104 0.01619 -0.0163 0.9108 0.0015
-10.000 -0.9843 0.01998 0.01492 -0.0142 0.8967 0.0015
-9.500 -0.9534 0.01809 0.01271 -0.0109 0.8775 0.0015
-9.250 -0.9352 0.01731 0.01180 -0.0096 0.8709 0.0015
-9.000 -0.9161 0.01654 0.01092 -0.0085 0.8649 0.0016
-8.750 -0.8964 0.01582 0.01007 -0.0074 0.8595 0.0016
-8.500 -0.8756 0.01515 0.00930 -0.0065 0.8546 0.0016
-8.250 -0.8538 0.01458 0.00861 -0.0057 0.8499 0.0016
-8.000 -0.8317 0.01401 0.00795 -0.0050 0.8459 0.0017
-7.750 -0.8086 0.01352 0.00738 -0.0044 0.8422 0.0017
-7.500 -0.7851 0.01306 0.00685 -0.0038 0.8383 0.0018
-7.250 -0.7611 0.01265 0.00636 -0.0033 0.8346 0.0018
-7.000 -0.7374 0.01219 0.00581 -0.0028 0.8313 0.0020
-6.750 -0.7127 0.01180 0.00537 -0.0024 0.8281 0.0025
-6.250 -0.6628 0.01108 0.00460 -0.0018 0.8216 0.0061
-6.000 -0.6378 0.01075 0.00428 -0.0015 0.8186 0.0105
-5.750 -0.6118 0.01050 0.00400 -0.0013 0.8158 0.0138
-5.500 -0.5859 0.01021 0.00374 -0.0011 0.8128 0.0189
-5.250 -0.5602 0.00991 0.00348 -0.0010 0.8098 0.0281
-5.000 -0.5349 0.00956 0.00321 -0.0007 0.8068 0.0454
-4.750 -0.5098 0.00919 0.00293 -0.0005 0.8041 0.0710
-4.500 -0.4841 0.00886 0.00270 -0.0003 0.8012 0.0970
-4.250 -0.4577 0.00859 0.00251 -0.0003 0.7981 0.1186
-4.000 -0.4316 0.00830 0.00231 -0.0002 0.7950 0.1464
-3.750 -0.4061 0.00795 0.00211 0.0000 0.7920 0.1875
-3.500 -0.3811 0.00752 0.00190 0.0002 0.7891 0.2443
-3.250 -0.3548 0.00722 0.00173 0.0003 0.7858 0.2848
-3.000 -0.3286 0.00690 0.00158 0.0004 0.7822 0.3321
-2.750 -0.3026 0.00658 0.00143 0.0005 0.7786 0.3821
-2.500 -0.2763 0.00630 0.00130 0.0005 0.7753 0.4314
-2.250 -0.2497 0.00601 0.00118 0.0006 0.7714 0.4797
-2.000 -0.2228 0.00578 0.00108 0.0006 0.7672 0.5214
-1.750 -0.1958 0.00559 0.00100 0.0006 0.7630 0.5606
-1.500 -0.1684 0.00541 0.00094 0.0006 0.7583 0.5959
-1.250 -0.1409 0.00526 0.00089 0.0006 0.7531 0.6289
-1.000 -0.1134 0.00516 0.00086 0.0005 0.7482 0.6580
-0.750 -0.0851 0.00509 0.00085 0.0004 0.7423 0.6796
-0.500 -0.0569 0.00506 0.00084 0.0003 0.7357 0.6954
-0.250 -0.0284 0.00504 0.00084 0.0001 0.7278 0.7081
0.000 0.0000 0.00504 0.00084 0.0000 0.7189 0.7189
0.250 0.0284 0.00504 0.00084 -0.0001 0.7081 0.7278
0.500 0.0569 0.00506 0.00084 -0.0003 0.6953 0.7357
0.750 0.0851 0.00509 0.00085 -0.0004 0.6796 0.7422
1.000 0.1134 0.00516 0.00086 -0.0005 0.6577 0.7482
1.250 0.1409 0.00526 0.00089 -0.0005 0.6289 0.7531
1.500 0.1684 0.00541 0.00094 -0.0006 0.5958 0.7583
1.750 0.1958 0.00559 0.00100 -0.0006 0.5608 0.7630
2.000 0.2228 0.00578 0.00108 -0.0006 0.5216 0.7672
2.250 0.2497 0.00601 0.00118 -0.0006 0.4793 0.7714
2.500 0.2763 0.00630 0.00130 -0.0005 0.4310 0.7753
2.750 0.3026 0.00658 0.00143 -0.0005 0.3820 0.7787
3.000 0.3287 0.00690 0.00158 -0.0004 0.3320 0.7822
3.250 0.3548 0.00722 0.00173 -0.0003 0.2846 0.7857
3.500 0.3812 0.00752 0.00190 -0.0003 0.2446 0.7891
3.750 0.4064 0.00792 0.00210 -0.0001 0.1906 0.7920
4.000 0.4318 0.00829 0.00231 0.0001 0.1469 0.7950
4.250 0.4579 0.00859 0.00251 0.0002 0.1185 0.7981
4.500 0.4843 0.00886 0.00270 0.0003 0.0972 0.8012
4.750 0.5102 0.00918 0.00293 0.0004 0.0721 0.8040
5.000 0.5354 0.00954 0.00320 0.0007 0.0474 0.8068
5.250 0.5605 0.00991 0.00348 0.0009 0.0281 0.8098
5.500 0.5863 0.01022 0.00374 0.0011 0.0186 0.8128
5.750 0.6122 0.01050 0.00401 0.0012 0.0138 0.8159
6.000 0.6382 0.01075 0.00427 0.0014 0.0107 0.8186
6.250 0.6633 0.01108 0.00460 0.0017 0.0061 0.8215
6.500 0.6883 0.01143 0.00497 0.0020 0.0035 0.8247
6.750 0.7132 0.01180 0.00537 0.0023 0.0025 0.8281
7.250 0.7617 0.01265 0.00636 0.0032 0.0018 0.8345
7.500 0.7857 0.01306 0.00684 0.0037 0.0018 0.8382
7.750 0.8093 0.01353 0.00738 0.0042 0.0017 0.8421
8.000 0.8324 0.01403 0.00796 0.0048 0.0017 0.8457
8.250 0.8546 0.01458 0.00862 0.0056 0.0016 0.8498
8.500 0.8762 0.01520 0.00935 0.0064 0.0016 0.8545
8.750 0.8975 0.01581 0.01006 0.0072 0.0016 0.8593
9.000 0.9169 0.01657 0.01095 0.0083 0.0015 0.8647
9.250 0.9358 0.01737 0.01188 0.0095 0.0015 0.8707
9.500 0.9543 0.01813 0.01276 0.0107 0.0015 0.8774
9.750 0.9708 0.01905 0.01382 0.0122 0.0015 0.8859
10.000 0.9853 0.02004 0.01500 0.0140 0.0015 0.8963
10.250 0.9994 0.02093 0.01604 0.0158 0.0015 0.9097
10.500 1.0093 0.02201 0.01735 0.0183 0.0015 0.9325
10.750 1.0275 0.02362 0.01923 0.0185 0.0015 0.9801
11.000 1.0351 0.02490 0.02065 0.0208 0.0015 1.0000
11.250 1.0368 0.02648 0.02243 0.0238 0.0015 1.0000
11.500 1.0364 0.02829 0.02442 0.0265 0.0015 1.0000
11.750 1.0393 0.02982 0.02609 0.0286 0.0015 1.0000
12.000 1.0342 0.03215 0.02861 0.0309 0.0015 1.0000
12.250 1.0292 0.03454 0.03118 0.0327 0.0015 1.0000
12.500 1.0209 0.03738 0.03422 0.0341 0.0015 1.0000
12.750 1.0094 0.04074 0.03776 0.0350 0.0015 1.0000
13.000 0.9968 0.04450 0.04170 0.0351 0.0015 1.0000
13.250 0.9849 0.04855 0.04591 0.0344 0.0015 1.0000
13.500 0.9630 0.05457 0.05213 0.0320 0.0015 1.0000
13.750 0.9468 0.06067 0.05839 0.0286 0.0015 1.0000
14.000 0.9275 0.06837 0.06624 0.0236 0.0015 1.0000
14.250 0.8995 0.07932 0.07736 0.0162 0.0015 1.0000
14.500 0.8645 0.09326 0.09147 0.0078 0.0015 1.0000
14.750 0.8426 0.10379 0.10207 0.0022 0.0016 1.0000
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Polar data table (+)
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