EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 297 AIRFOIL (e297-il) Reynolds number: 500,000 Max Cl/Cd: 51.09 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e297-il-500000-n5.txt Download as CSV file: xf-e297-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.8315 0.08056 0.07813 -0.0170 1.0000 0.0024
-13.250 -0.8537 0.07070 0.06811 -0.0238 1.0000 0.0024
-13.000 -0.8761 0.06242 0.05964 -0.0293 1.0000 0.0024
-12.750 -0.8975 0.05567 0.05268 -0.0329 1.0000 0.0024
-12.500 -0.9178 0.05004 0.04684 -0.0349 1.0000 0.0024
-12.250 -0.9329 0.04568 0.04227 -0.0355 1.0000 0.0023
-12.000 -0.9475 0.04172 0.03807 -0.0351 1.0000 0.0023
-11.750 -0.9580 0.03845 0.03457 -0.0339 1.0000 0.0023
-11.500 -0.9647 0.03570 0.03160 -0.0323 1.0000 0.0023
-11.250 -0.9685 0.03328 0.02896 -0.0303 1.0000 0.0023
-11.000 -0.9713 0.03096 0.02640 -0.0280 1.0000 0.0023
-10.750 -0.9693 0.02913 0.02438 -0.0256 1.0000 0.0024
-10.500 -0.9654 0.02746 0.02252 -0.0232 1.0000 0.0024
-10.250 -0.9591 0.02595 0.02083 -0.0207 1.0000 0.0024
-10.000 -0.9497 0.02453 0.01923 -0.0186 1.0000 0.0024
-9.750 -0.9369 0.02321 0.01776 -0.0169 1.0000 0.0024
-9.500 -0.9226 0.02191 0.01629 -0.0155 0.9943 0.0025
-9.250 -0.8956 0.02060 0.01481 -0.0166 0.9589 0.0025
-9.000 -0.8734 0.01950 0.01354 -0.0164 0.9386 0.0026
-8.750 -0.8563 0.01861 0.01248 -0.0149 0.9225 0.0027
-8.500 -0.8390 0.01781 0.01150 -0.0134 0.9111 0.0028
-8.250 -0.8204 0.01710 0.01064 -0.0121 0.9021 0.0029
-8.000 -0.8009 0.01639 0.00980 -0.0109 0.8947 0.0031
-7.750 -0.7804 0.01578 0.00907 -0.0098 0.8880 0.0033
-7.500 -0.7588 0.01523 0.00840 -0.0090 0.8823 0.0036
-7.250 -0.7379 0.01454 0.00761 -0.0079 0.8769 0.0046
-6.750 -0.6926 0.01356 0.00655 -0.0066 0.8677 0.0092
-6.500 -0.6686 0.01319 0.00609 -0.0061 0.8633 0.0128
-6.250 -0.6450 0.01281 0.00569 -0.0056 0.8595 0.0177
-6.000 -0.6211 0.01238 0.00531 -0.0051 0.8557 0.0272
-5.750 -0.5974 0.01193 0.00494 -0.0047 0.8517 0.0431
-5.500 -0.5734 0.01152 0.00458 -0.0042 0.8480 0.0613
-5.000 -0.5240 0.01081 0.00397 -0.0036 0.8413 0.1022
-4.750 -0.4991 0.01045 0.00367 -0.0033 0.8376 0.1282
-4.500 -0.4748 0.01003 0.00340 -0.0029 0.8343 0.1660
-4.250 -0.4515 0.00952 0.00311 -0.0025 0.8313 0.2244
-4.000 -0.4273 0.00905 0.00286 -0.0022 0.8277 0.2807
-3.750 -0.4027 0.00864 0.00264 -0.0019 0.8241 0.3324
-3.500 -0.3781 0.00825 0.00243 -0.0015 0.8207 0.3875
-3.250 -0.3537 0.00787 0.00222 -0.0011 0.8176 0.4456
-3.000 -0.3286 0.00751 0.00206 -0.0008 0.8140 0.5011
-2.750 -0.3033 0.00721 0.00194 -0.0005 0.8102 0.5518
-2.500 -0.2773 0.00699 0.00185 -0.0002 0.8067 0.5937
-2.250 -0.2510 0.00684 0.00177 0.0000 0.8034 0.6290
-2.000 -0.2238 0.00673 0.00176 0.0001 0.7992 0.6580
-1.750 -0.1964 0.00667 0.00175 0.0002 0.7950 0.6826
-1.500 -0.1689 0.00665 0.00174 0.0003 0.7912 0.7015
-1.250 -0.1409 0.00664 0.00173 0.0003 0.7869 0.7156
-1.000 -0.1127 0.00663 0.00173 0.0002 0.7818 0.7269
-0.750 -0.0847 0.00663 0.00171 0.0002 0.7771 0.7368
-0.500 -0.0564 0.00663 0.00172 0.0001 0.7717 0.7457
-0.250 -0.0282 0.00663 0.00171 0.0001 0.7659 0.7531
0.000 0.0000 0.00663 0.00170 0.0000 0.7603 0.7603
0.250 0.0282 0.00663 0.00171 -0.0001 0.7531 0.7660
0.500 0.0564 0.00663 0.00172 -0.0001 0.7456 0.7717
0.750 0.0847 0.00663 0.00171 -0.0002 0.7368 0.7771
1.000 0.1127 0.00663 0.00173 -0.0002 0.7269 0.7818
1.250 0.1409 0.00664 0.00173 -0.0003 0.7156 0.7869
1.500 0.1689 0.00665 0.00174 -0.0003 0.7016 0.7912
1.750 0.1964 0.00667 0.00175 -0.0002 0.6826 0.7950
2.000 0.2239 0.00673 0.00176 -0.0002 0.6581 0.7992
2.250 0.2510 0.00684 0.00177 0.0000 0.6289 0.8034
2.500 0.2774 0.00699 0.00185 0.0002 0.5937 0.8066
2.750 0.3033 0.00721 0.00194 0.0005 0.5517 0.8102
3.000 0.3287 0.00751 0.00206 0.0008 0.5016 0.8140
3.250 0.3538 0.00787 0.00222 0.0011 0.4458 0.8177
3.500 0.3783 0.00825 0.00243 0.0015 0.3871 0.8207
3.750 0.4029 0.00864 0.00264 0.0018 0.3322 0.8240
4.000 0.4274 0.00906 0.00286 0.0021 0.2789 0.8276
4.500 0.4751 0.01003 0.00340 0.0029 0.1664 0.8343
4.750 0.4994 0.01045 0.00367 0.0032 0.1285 0.8376
5.000 0.5244 0.01081 0.00397 0.0035 0.1024 0.8413
5.500 0.5739 0.01152 0.00459 0.0041 0.0613 0.8480
5.750 0.5979 0.01194 0.00494 0.0046 0.0426 0.8516
6.000 0.6217 0.01238 0.00532 0.0050 0.0276 0.8556
6.250 0.6456 0.01281 0.00570 0.0054 0.0177 0.8595
6.500 0.6694 0.01319 0.00610 0.0059 0.0129 0.8632
6.750 0.6933 0.01357 0.00655 0.0064 0.0093 0.8676
7.250 0.7388 0.01455 0.00762 0.0078 0.0045 0.8768
7.500 0.7598 0.01523 0.00840 0.0088 0.0036 0.8821
7.750 0.7815 0.01579 0.00908 0.0096 0.0033 0.8878
8.000 0.8020 0.01641 0.00982 0.0107 0.0031 0.8945
8.250 0.8216 0.01712 0.01066 0.0118 0.0029 0.9018
8.500 0.8400 0.01787 0.01155 0.0132 0.0028 0.9108
8.750 0.8577 0.01862 0.01249 0.0146 0.0027 0.9220
9.000 0.8748 0.01954 0.01357 0.0161 0.0026 0.9378
9.250 0.8965 0.02066 0.01487 0.0164 0.0025 0.9580
9.500 0.9236 0.02196 0.01636 0.0153 0.0025 0.9904
9.750 0.9386 0.02324 0.01778 0.0166 0.0024 1.0000
10.000 0.9514 0.02458 0.01928 0.0182 0.0024 1.0000
10.250 0.9616 0.02597 0.02084 0.0202 0.0024 1.0000
10.500 0.9677 0.02749 0.02254 0.0227 0.0024 1.0000
10.750 0.9706 0.02928 0.02455 0.0253 0.0023 1.0000
11.000 0.9728 0.03109 0.02655 0.0276 0.0023 1.0000
11.250 0.9712 0.03326 0.02894 0.0299 0.0023 1.0000
11.500 0.9666 0.03576 0.03167 0.0319 0.0023 1.0000
11.750 0.9601 0.03852 0.03465 0.0335 0.0023 1.0000
12.000 0.9472 0.04208 0.03846 0.0347 0.0023 1.0000
12.250 0.9344 0.04583 0.04243 0.0351 0.0024 1.0000
12.500 0.9190 0.05024 0.04705 0.0345 0.0024 1.0000
12.750 0.8998 0.05573 0.05275 0.0325 0.0024 1.0000
13.000 0.8784 0.06250 0.05972 0.0288 0.0024 1.0000
13.250 0.8578 0.07040 0.06780 0.0236 0.0024 1.0000
13.500 0.8285 0.08205 0.07964 0.0156 0.0024 1.0000
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Polar data table (+)
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