EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 297 AIRFOIL (e297-il) Reynolds number: 100,000 Max Cl/Cd: 43.07 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e297-il-100000.txt Download as CSV file: xf-e297-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5018 0.12612 0.12169 -0.0054 1.0000 0.1155
-11.750 -0.5340 0.12147 0.11711 -0.0114 1.0000 0.1171
-11.500 -0.6001 0.12107 0.11626 -0.0033 1.0000 0.1117
-11.250 -0.5274 0.10353 0.09919 -0.0154 1.0000 0.0719
-11.000 -0.5525 0.09193 0.08765 -0.0215 1.0000 0.0585
-9.750 -0.7649 0.06444 0.05931 -0.0349 1.0000 0.0501
-9.500 -0.7782 0.06049 0.05520 -0.0330 1.0000 0.0492
-9.250 -0.7865 0.05627 0.05077 -0.0313 1.0000 0.0472
-9.000 -0.7964 0.05155 0.04568 -0.0288 1.0000 0.0446
-8.750 -0.8097 0.04673 0.03998 -0.0246 1.0000 0.0413
-8.500 -0.8021 0.04403 0.03681 -0.0221 1.0000 0.0405
-8.250 -0.7923 0.04098 0.03336 -0.0199 1.0000 0.0402
-8.000 -0.7823 0.03668 0.02865 -0.0178 1.0000 0.0407
-7.750 -0.7670 0.03312 0.02486 -0.0162 1.0000 0.0423
-7.500 -0.7534 0.03144 0.02310 -0.0143 1.0000 0.0470
-7.250 -0.7418 0.03009 0.02132 -0.0112 1.0000 0.0519
-7.000 -0.7232 0.02712 0.01842 -0.0097 1.0000 0.0580
-6.750 -0.7113 0.02565 0.01684 -0.0070 1.0000 0.0675
-6.500 -0.6981 0.02436 0.01536 -0.0042 1.0000 0.0774
-6.250 -0.6880 0.02295 0.01407 -0.0015 1.0000 0.0919
-6.000 -0.6792 0.02154 0.01284 0.0016 1.0000 0.1083
-5.750 -0.6722 0.02021 0.01171 0.0050 1.0000 0.1363
-5.500 -0.6670 0.01876 0.01068 0.0084 1.0000 0.1894
-5.250 -0.6634 0.01713 0.00979 0.0118 1.0000 0.2871
-5.000 -0.6594 0.01577 0.00928 0.0155 1.0000 0.4248
-4.750 -0.6509 0.01511 0.00928 0.0195 1.0000 0.5533
-4.500 -0.6379 0.01521 0.00967 0.0233 1.0000 0.6404
-4.250 -0.6235 0.01565 0.01012 0.0270 1.0000 0.6952
-4.000 -0.6094 0.01616 0.01052 0.0305 1.0000 0.7344
-3.750 -0.5952 0.01672 0.01093 0.0343 1.0000 0.7640
-3.500 -0.5816 0.01719 0.01130 0.0380 1.0000 0.7901
-3.250 -0.5666 0.01771 0.01173 0.0418 1.0000 0.8116
-3.000 -0.5527 0.01804 0.01194 0.0454 1.0000 0.8332
-2.750 -0.5356 0.01840 0.01220 0.0485 1.0000 0.8529
-2.500 -0.5192 0.01863 0.01231 0.0513 1.0000 0.8733
-2.250 -0.4894 0.01909 0.01260 0.0518 1.0000 0.8909
-2.000 -0.4508 0.01956 0.01292 0.0503 1.0000 0.9075
-1.750 -0.4008 0.02006 0.01324 0.0462 1.0000 0.9212
-1.500 -0.3410 0.02052 0.01352 0.0398 1.0000 0.9323
-1.250 -0.2891 0.02078 0.01365 0.0346 1.0000 0.9433
-1.000 -0.2442 0.02096 0.01372 0.0304 1.0000 0.9546
-0.750 -0.1778 0.02116 0.01381 0.0219 0.9968 0.9610
-0.500 -0.1211 0.02135 0.01394 0.0152 0.9920 0.9690
-0.250 -0.0590 0.02138 0.01392 0.0073 0.9869 0.9750
0.000 -0.0001 0.02152 0.01405 0.0000 0.9816 0.9816
0.250 0.0590 0.02137 0.01392 -0.0073 0.9750 0.9869
0.500 0.1210 0.02134 0.01393 -0.0151 0.9691 0.9920
0.750 0.1778 0.02115 0.01380 -0.0219 0.9610 0.9968
1.000 0.2440 0.02095 0.01371 -0.0303 0.9547 1.0000
1.250 0.2886 0.02078 0.01364 -0.0345 0.9434 1.0000
1.500 0.3408 0.02051 0.01350 -0.0398 0.9324 1.0000
1.750 0.4005 0.02004 0.01323 -0.0461 0.9213 1.0000
2.000 0.4507 0.01954 0.01290 -0.0502 0.9076 1.0000
2.250 0.4891 0.01907 0.01258 -0.0518 0.8909 1.0000
2.500 0.5186 0.01861 0.01230 -0.0512 0.8733 1.0000
2.750 0.5351 0.01840 0.01219 -0.0484 0.8530 1.0000
3.000 0.5520 0.01803 0.01193 -0.0452 0.8332 1.0000
3.250 0.5658 0.01771 0.01172 -0.0417 0.8117 1.0000
3.500 0.5808 0.01720 0.01131 -0.0379 0.7904 1.0000
3.750 0.5943 0.01672 0.01093 -0.0341 0.7641 1.0000
4.000 0.6087 0.01615 0.01052 -0.0304 0.7350 1.0000
4.250 0.6226 0.01565 0.01012 -0.0268 0.6957 1.0000
4.500 0.6369 0.01520 0.00966 -0.0232 0.6408 1.0000
4.750 0.6500 0.01509 0.00926 -0.0193 0.5547 1.0000
5.000 0.6586 0.01574 0.00926 -0.0154 0.4273 1.0000
5.250 0.6628 0.01709 0.00977 -0.0117 0.2897 1.0000
5.500 0.6662 0.01873 0.01066 -0.0082 0.1903 1.0000
5.750 0.6715 0.02018 0.01168 -0.0048 0.1368 1.0000
6.000 0.6784 0.02151 0.01281 -0.0015 0.1088 1.0000
6.250 0.6872 0.02291 0.01404 0.0016 0.0921 1.0000
6.500 0.6973 0.02434 0.01532 0.0043 0.0776 1.0000
6.750 0.7104 0.02561 0.01680 0.0072 0.0677 1.0000
7.000 0.7224 0.02709 0.01839 0.0098 0.0580 1.0000
7.250 0.7411 0.03007 0.02129 0.0113 0.0520 1.0000
7.500 0.7533 0.03147 0.02312 0.0143 0.0474 1.0000
7.750 0.7670 0.03311 0.02484 0.0162 0.0423 1.0000
8.000 0.7823 0.03681 0.02877 0.0177 0.0407 1.0000
8.250 0.7927 0.04103 0.03341 0.0198 0.0402 1.0000
8.500 0.8017 0.04438 0.03718 0.0220 0.0404 1.0000
8.750 0.8103 0.04671 0.03999 0.0246 0.0414 1.0000
9.000 0.7969 0.05165 0.04578 0.0287 0.0446 1.0000
9.250 0.7866 0.05636 0.05087 0.0312 0.0469 1.0000
9.500 0.7776 0.06055 0.05528 0.0329 0.0490 1.0000
9.750 0.7673 0.06462 0.05948 0.0345 0.0502 1.0000
10.000 0.7546 0.06863 0.06358 0.0358 0.0509 1.0000
10.250 0.6780 0.06396 0.05934 0.0388 0.0536 1.0000
10.500 0.6438 0.06929 0.06484 0.0370 0.0540 1.0000
10.750 0.6072 0.07668 0.07236 0.0326 0.0544 1.0000
11.000 0.5523 0.09212 0.08784 0.0212 0.0586 1.0000
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Polar data table (+)
Polar graphs
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