EPPLER 657 AIRFOIL (e657-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 657 AIRFOIL (e657-il) Reynolds number: 500,000 Max Cl/Cd: 126.17 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e657-il-500000.txt Download as CSV file: xf-e657-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 657 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0479 0.09251 0.08907 -0.1234 0.8027 0.0220
-11.000 -0.0704 0.08318 0.07980 -0.1289 0.8005 0.0232
-10.750 -0.0634 0.08107 0.07768 -0.1292 0.7986 0.0235
-10.500 -0.0550 0.07926 0.07586 -0.1296 0.7966 0.0238
-10.250 -0.0503 0.07661 0.07320 -0.1307 0.7946 0.0241
-10.000 -0.0490 0.07332 0.06990 -0.1323 0.7924 0.0245
-9.750 -0.0522 0.06922 0.06585 -0.1343 0.7904 0.0249
-9.500 -0.0598 0.06420 0.06087 -0.1371 0.7883 0.0255
-9.250 -0.0881 0.05458 0.05127 -0.1449 0.7856 0.0253
-9.000 -0.1183 0.04908 0.04567 -0.1470 0.7828 0.0253
-8.750 -0.1414 0.04601 0.04249 -0.1452 0.7803 0.0254
-8.500 -0.1599 0.04298 0.03928 -0.1429 0.7781 0.0260
-8.000 -0.2328 0.02433 0.01859 -0.1316 0.7732 0.0129
-7.750 -0.2156 0.02238 0.01646 -0.1306 0.7715 0.0127
-7.500 -0.1963 0.02072 0.01458 -0.1298 0.7699 0.0124
-7.250 -0.1749 0.01938 0.01305 -0.1291 0.7683 0.0123
-7.000 -0.1523 0.01824 0.01174 -0.1285 0.7668 0.0122
-6.750 -0.1290 0.01729 0.01065 -0.1279 0.7653 0.0124
-6.500 -0.1052 0.01651 0.00977 -0.1275 0.7637 0.0125
-6.250 -0.0809 0.01584 0.00900 -0.1271 0.7622 0.0128
-6.000 -0.0564 0.01529 0.00836 -0.1267 0.7607 0.0131
-5.750 -0.0334 0.01464 0.00770 -0.1263 0.7592 0.0140
-5.500 -0.0086 0.01420 0.00725 -0.1260 0.7580 0.0152
-5.250 0.0159 0.01372 0.00674 -0.1257 0.7565 0.0167
-5.000 0.0416 0.01338 0.00639 -0.1256 0.7548 0.0192
-4.750 0.0670 0.01295 0.00599 -0.1254 0.7531 0.0248
-4.500 0.0927 0.01253 0.00566 -0.1253 0.7515 0.0424
-4.250 0.1189 0.01219 0.00544 -0.1254 0.7500 0.0667
-4.000 0.1457 0.01188 0.00525 -0.1255 0.7485 0.0987
-3.750 0.1725 0.01155 0.00508 -0.1258 0.7469 0.1444
-3.500 0.1994 0.01119 0.00495 -0.1261 0.7455 0.2102
-3.250 0.2264 0.01084 0.00486 -0.1265 0.7442 0.2911
-3.000 0.2534 0.01055 0.00485 -0.1268 0.7426 0.3790
-2.750 0.2796 0.01015 0.00479 -0.1271 0.7411 0.4757
-2.500 0.3060 0.00982 0.00479 -0.1272 0.7394 0.5749
-2.250 0.3325 0.00964 0.00487 -0.1271 0.7375 0.6556
-2.000 0.3595 0.00962 0.00497 -0.1269 0.7356 0.7083
-1.750 0.3869 0.00964 0.00503 -0.1268 0.7337 0.7384
-1.500 0.4141 0.00970 0.00512 -0.1266 0.7319 0.7597
-1.250 0.4421 0.00981 0.00521 -0.1265 0.7302 0.7767
-1.000 0.4708 0.00995 0.00530 -0.1266 0.7286 0.7909
-0.750 0.4995 0.01015 0.00545 -0.1267 0.7268 0.8026
-0.500 0.5263 0.01031 0.00559 -0.1265 0.7247 0.8127
-0.250 0.5530 0.01042 0.00570 -0.1263 0.7223 0.8222
0.000 0.5787 0.01049 0.00579 -0.1259 0.7197 0.8288
0.250 0.6062 0.01055 0.00582 -0.1258 0.7173 0.8368
0.500 0.6329 0.01056 0.00583 -0.1255 0.7150 0.8427
0.750 0.6607 0.01060 0.00583 -0.1254 0.7129 0.8496
1.000 0.6893 0.01065 0.00585 -0.1255 0.7109 0.8561
1.250 0.7134 0.01074 0.00596 -0.1247 0.7082 0.8617
1.500 0.7391 0.01078 0.00603 -0.1244 0.7050 0.8686
1.750 0.7630 0.01075 0.00603 -0.1236 0.7019 0.8738
2.000 0.7893 0.01071 0.00598 -0.1232 0.6991 0.8792
2.250 0.8194 0.01067 0.00591 -0.1238 0.6965 0.8842
2.500 0.8483 0.01067 0.00586 -0.1240 0.6940 0.8878
2.750 0.8699 0.01064 0.00591 -0.1229 0.6903 0.8921
3.000 0.8953 0.01061 0.00592 -0.1225 0.6865 0.8968
3.250 0.9246 0.01054 0.00584 -0.1230 0.6830 0.9011
3.500 0.9513 0.01041 0.00569 -0.1227 0.6798 0.9045
3.750 0.9756 0.01038 0.00568 -0.1221 0.6758 0.9086
4.000 0.9998 0.01032 0.00569 -0.1216 0.6709 0.9132
4.250 1.0274 0.01022 0.00559 -0.1217 0.6666 0.9168
4.500 1.0538 0.01011 0.00546 -0.1214 0.6628 0.9202
4.750 1.0741 0.01008 0.00552 -0.1200 0.6569 0.9249
5.000 1.0995 0.01000 0.00547 -0.1197 0.6512 0.9290
5.250 1.1239 0.00991 0.00539 -0.1191 0.6456 0.9328
5.500 1.1427 0.00985 0.00541 -0.1175 0.6380 0.9376
5.750 1.1665 0.00979 0.00534 -0.1168 0.6309 0.9421
6.000 1.1847 0.00976 0.00538 -0.1150 0.6211 0.9472
6.250 1.2033 0.00974 0.00539 -0.1133 0.6112 0.9526
6.500 1.2226 0.00977 0.00542 -0.1119 0.5998 0.9579
6.750 1.2377 0.00981 0.00546 -0.1095 0.5862 0.9642
7.000 1.2517 0.00994 0.00558 -0.1071 0.5700 0.9720
7.250 1.2708 0.01019 0.00581 -0.1059 0.5508 0.9841
7.500 1.2863 0.01059 0.00614 -0.1043 0.5289 1.0000
7.750 1.2977 0.01116 0.00661 -0.1020 0.5069 1.0000
8.000 1.3071 0.01183 0.00721 -0.0995 0.4831 1.0000
8.500 1.3214 0.01355 0.00876 -0.0943 0.4395 1.0000
8.750 1.3276 0.01456 0.00969 -0.0917 0.4186 1.0000
9.000 1.3317 0.01573 0.01078 -0.0891 0.3978 1.0000
9.250 1.3372 0.01690 0.01188 -0.0867 0.3773 1.0000
9.500 1.3431 0.01811 0.01302 -0.0845 0.3576 1.0000
9.750 1.3486 0.01939 0.01423 -0.0824 0.3383 1.0000
10.000 1.3532 0.02075 0.01551 -0.0802 0.3192 1.0000
10.250 1.3584 0.02211 0.01681 -0.0781 0.3013 1.0000
10.500 1.3647 0.02345 0.01809 -0.0763 0.2835 1.0000
10.750 1.3714 0.02479 0.01937 -0.0745 0.2660 1.0000
11.000 1.3774 0.02621 0.02073 -0.0728 0.2483 1.0000
11.250 1.3844 0.02760 0.02206 -0.0712 0.2324 1.0000
11.500 1.3904 0.02910 0.02351 -0.0696 0.2156 1.0000
11.750 1.3977 0.03054 0.02490 -0.0682 0.2008 1.0000
12.000 1.4043 0.03208 0.02639 -0.0668 0.1860 1.0000
12.250 1.4113 0.03362 0.02788 -0.0655 0.1716 1.0000
12.500 1.4181 0.03522 0.02945 -0.0642 0.1589 1.0000
12.750 1.4251 0.03684 0.03104 -0.0631 0.1468 1.0000
13.000 1.4309 0.03860 0.03276 -0.0619 0.1349 1.0000
13.250 1.4387 0.04023 0.03438 -0.0609 0.1239 1.0000
13.500 1.4458 0.04195 0.03609 -0.0600 0.1135 1.0000
13.750 1.4521 0.04380 0.03793 -0.0591 0.1042 1.0000
14.000 1.4573 0.04578 0.03989 -0.0582 0.0949 1.0000
14.250 1.4630 0.04775 0.04186 -0.0574 0.0864 1.0000
14.500 1.4692 0.04973 0.04384 -0.0567 0.0785 1.0000
14.750 1.4731 0.05198 0.04609 -0.0560 0.0714 1.0000
15.000 1.4772 0.05426 0.04837 -0.0554 0.0644 1.0000
15.250 1.4819 0.05653 0.05067 -0.0549 0.0583 1.0000
15.500 1.4846 0.05907 0.05322 -0.0544 0.0528 1.0000
15.750 1.4878 0.06161 0.05579 -0.0540 0.0480 1.0000
16.000 1.4906 0.06426 0.05849 -0.0538 0.0436 1.0000
16.250 1.4910 0.06724 0.06149 -0.0536 0.0396 1.0000
16.500 1.4940 0.06998 0.06430 -0.0535 0.0361 1.0000
17.000 1.4953 0.07621 0.07063 -0.0537 0.0303 1.0000
17.250 1.4929 0.07984 0.07431 -0.0540 0.0281 1.0000
17.500 1.4943 0.08303 0.07760 -0.0544 0.0259 1.0000
17.750 1.4923 0.08672 0.08135 -0.0550 0.0240 1.0000
18.000 1.4922 0.09021 0.08492 -0.0557 0.0219 1.0000
18.250 1.4902 0.09404 0.08882 -0.0565 0.0204 1.0000
18.500 1.4851 0.09840 0.09326 -0.0576 0.0191 1.0000
18.750 1.4846 0.10212 0.09709 -0.0586 0.0178 1.0000
19.000 1.4809 0.10636 0.10140 -0.0599 0.0166 1.0000
19.250 1.4747 0.11107 0.10621 -0.0615 0.0157 1.0000
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Polar data table (+)
Polar graphs
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