EPPLER 657 AIRFOIL (e657-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 657 AIRFOIL (e657-il) Reynolds number: 500,000 Max Cl/Cd: 117.79 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e657-il-500000-n5.txt Download as CSV file: xf-e657-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2270 0.07235 0.06867 -0.1230 0.7687 0.0060
-12.000 -0.2964 0.05378 0.04988 -0.1335 0.7666 0.0059
-11.750 -0.3266 0.04453 0.04042 -0.1408 0.7639 0.0058
-11.500 -0.3440 0.03984 0.03556 -0.1436 0.7612 0.0058
-11.250 -0.3638 0.03595 0.03144 -0.1442 0.7588 0.0058
-11.000 -0.3721 0.03356 0.02892 -0.1434 0.7567 0.0058
-10.750 -0.3856 0.03098 0.02613 -0.1414 0.7544 0.0058
-10.500 -0.3930 0.02911 0.02409 -0.1388 0.7522 0.0058
-10.250 -0.3986 0.02761 0.02240 -0.1356 0.7501 0.0058
-10.000 -0.3952 0.02600 0.02056 -0.1334 0.7482 0.0058
-9.750 -0.3867 0.02457 0.01891 -0.1317 0.7465 0.0058
-9.500 -0.3747 0.02327 0.01739 -0.1303 0.7448 0.0058
-9.250 -0.3599 0.02210 0.01602 -0.1291 0.7431 0.0058
-9.000 -0.3431 0.02103 0.01478 -0.1281 0.7416 0.0059
-8.750 -0.3244 0.02009 0.01370 -0.1273 0.7401 0.0059
-8.500 -0.3051 0.01914 0.01262 -0.1265 0.7387 0.0060
-8.250 -0.2853 0.01822 0.01159 -0.1257 0.7372 0.0060
-8.000 -0.2649 0.01733 0.01061 -0.1250 0.7358 0.0062
-7.750 -0.2425 0.01669 0.00988 -0.1246 0.7344 0.0062
-7.500 -0.2195 0.01609 0.00921 -0.1241 0.7330 0.0064
-7.250 -0.1957 0.01556 0.00861 -0.1238 0.7315 0.0066
-7.000 -0.1715 0.01507 0.00805 -0.1235 0.7300 0.0068
-6.750 -0.1468 0.01461 0.00751 -0.1233 0.7286 0.0071
-6.500 -0.1216 0.01420 0.00701 -0.1231 0.7274 0.0074
-6.250 -0.0960 0.01382 0.00655 -0.1230 0.7262 0.0078
-6.000 -0.0703 0.01344 0.00613 -0.1229 0.7251 0.0082
-5.750 -0.0445 0.01307 0.00575 -0.1228 0.7238 0.0089
-5.500 -0.0182 0.01277 0.00541 -0.1228 0.7224 0.0099
-5.250 0.0083 0.01247 0.00509 -0.1228 0.7209 0.0111
-5.000 0.0351 0.01221 0.00480 -0.1228 0.7194 0.0130
-4.750 0.0619 0.01193 0.00454 -0.1229 0.7181 0.0171
-4.500 0.0888 0.01167 0.00431 -0.1230 0.7168 0.0256
-4.250 0.1160 0.01143 0.00411 -0.1231 0.7154 0.0366
-4.000 0.1432 0.01120 0.00392 -0.1233 0.7141 0.0512
-3.750 0.1706 0.01096 0.00375 -0.1235 0.7127 0.0716
-3.500 0.1980 0.01069 0.00360 -0.1238 0.7115 0.1041
-3.250 0.2256 0.01044 0.00348 -0.1241 0.7103 0.1439
-3.000 0.2529 0.01021 0.00338 -0.1244 0.7089 0.1850
-2.750 0.2803 0.00997 0.00329 -0.1247 0.7074 0.2284
-2.500 0.3079 0.00974 0.00322 -0.1250 0.7059 0.2788
-2.250 0.3354 0.00945 0.00314 -0.1254 0.7043 0.3464
-2.000 0.3631 0.00914 0.00308 -0.1258 0.7026 0.4256
-1.750 0.3910 0.00882 0.00303 -0.1262 0.7010 0.5102
-1.500 0.4191 0.00859 0.00301 -0.1266 0.6994 0.5852
-1.250 0.4472 0.00844 0.00302 -0.1268 0.6978 0.6436
-1.000 0.4754 0.00838 0.00306 -0.1269 0.6961 0.6871
-0.750 0.5042 0.00839 0.00308 -0.1272 0.6945 0.7167
-0.500 0.5319 0.00840 0.00313 -0.1272 0.6925 0.7365
-0.250 0.5590 0.00842 0.00322 -0.1271 0.6903 0.7525
0.000 0.5863 0.00847 0.00330 -0.1270 0.6878 0.7665
0.250 0.6138 0.00853 0.00338 -0.1270 0.6853 0.7790
0.500 0.6418 0.00859 0.00343 -0.1271 0.6829 0.7902
0.750 0.6702 0.00864 0.00346 -0.1273 0.6805 0.8003
1.000 0.6996 0.00872 0.00347 -0.1277 0.6782 0.8099
1.250 0.7263 0.00877 0.00357 -0.1276 0.6753 0.8165
1.500 0.7542 0.00883 0.00363 -0.1278 0.6720 0.8240
1.750 0.7807 0.00886 0.00368 -0.1276 0.6687 0.8290
2.000 0.8084 0.00889 0.00370 -0.1276 0.6654 0.8341
2.250 0.8372 0.00892 0.00369 -0.1280 0.6624 0.8384
2.500 0.8629 0.00895 0.00378 -0.1277 0.6582 0.8415
2.750 0.8893 0.00898 0.00384 -0.1276 0.6538 0.8450
3.000 0.9164 0.00900 0.00387 -0.1276 0.6496 0.8487
3.250 0.9436 0.00904 0.00391 -0.1277 0.6451 0.8523
3.500 0.9694 0.00907 0.00398 -0.1274 0.6389 0.8553
3.750 0.9949 0.00909 0.00401 -0.1271 0.6329 0.8581
4.000 1.0202 0.00914 0.00410 -0.1268 0.6258 0.8610
4.250 1.0452 0.00920 0.00414 -0.1264 0.6180 0.8641
4.500 1.0703 0.00927 0.00424 -0.1261 0.6090 0.8672
4.750 1.0943 0.00936 0.00432 -0.1255 0.5985 0.8701
5.000 1.1156 0.00948 0.00441 -0.1244 0.5856 0.8728
5.250 1.1355 0.00964 0.00454 -0.1230 0.5702 0.8760
5.500 1.1537 0.00986 0.00473 -0.1214 0.5526 0.8796
5.750 1.1694 0.01016 0.00495 -0.1193 0.5323 0.8833
6.000 1.1797 0.01051 0.00522 -0.1161 0.5111 0.8867
6.250 1.1860 0.01091 0.00556 -0.1122 0.4915 0.8901
6.500 1.1933 0.01139 0.00598 -0.1087 0.4713 0.8937
6.750 1.2002 0.01194 0.00646 -0.1052 0.4516 0.8979
7.000 1.2055 0.01259 0.00704 -0.1017 0.4319 0.9019
7.250 1.2099 0.01328 0.00769 -0.0981 0.4138 0.9058
7.500 1.2149 0.01406 0.00843 -0.0948 0.3954 0.9101
7.750 1.2213 0.01488 0.00921 -0.0920 0.3778 0.9145
8.000 1.2267 0.01578 0.01007 -0.0891 0.3597 0.9191
8.250 1.2325 0.01671 0.01097 -0.0863 0.3425 0.9248
8.750 1.2442 0.01873 0.01291 -0.0812 0.3074 0.9430
9.000 1.2565 0.01973 0.01390 -0.0801 0.2911 0.9662
9.500 1.2746 0.02199 0.01605 -0.0769 0.2581 1.0000
9.750 1.2841 0.02315 0.01716 -0.0754 0.2424 1.0000
10.000 1.2939 0.02432 0.01827 -0.0740 0.2278 1.0000
10.250 1.3036 0.02550 0.01942 -0.0726 0.2136 1.0000
10.500 1.3132 0.02673 0.02060 -0.0713 0.1996 1.0000
10.750 1.3229 0.02796 0.02179 -0.0700 0.1865 1.0000
11.000 1.3321 0.02926 0.02305 -0.0687 0.1732 1.0000
11.250 1.3414 0.03058 0.02432 -0.0675 0.1604 1.0000
11.500 1.3498 0.03199 0.02569 -0.0662 0.1475 1.0000
11.750 1.3594 0.03335 0.02702 -0.0651 0.1361 1.0000
12.000 1.3681 0.03480 0.02844 -0.0640 0.1244 1.0000
12.250 1.3770 0.03627 0.02988 -0.0630 0.1136 1.0000
12.500 1.3861 0.03775 0.03135 -0.0620 0.1045 1.0000
12.750 1.3942 0.03935 0.03293 -0.0611 0.0961 1.0000
13.000 1.4040 0.04083 0.03443 -0.0603 0.0881 1.0000
13.250 1.4123 0.04248 0.03608 -0.0594 0.0812 1.0000
13.500 1.4195 0.04426 0.03785 -0.0586 0.0737 1.0000
13.750 1.4285 0.04591 0.03952 -0.0579 0.0676 1.0000
14.000 1.4351 0.04781 0.04143 -0.0572 0.0617 1.0000
14.250 1.4426 0.04966 0.04330 -0.0565 0.0561 1.0000
14.500 1.4491 0.05166 0.04533 -0.0560 0.0510 1.0000
14.750 1.4545 0.05381 0.04748 -0.0554 0.0460 1.0000
15.000 1.4607 0.05593 0.04964 -0.0549 0.0415 1.0000
15.250 1.4657 0.05819 0.05193 -0.0545 0.0375 1.0000
15.500 1.4699 0.06061 0.05438 -0.0542 0.0337 1.0000
15.750 1.4753 0.06294 0.05677 -0.0539 0.0308 1.0000
16.250 1.4824 0.06817 0.06210 -0.0536 0.0252 1.0000
16.500 1.4843 0.07105 0.06503 -0.0536 0.0229 1.0000
16.750 1.4871 0.07390 0.06795 -0.0537 0.0208 1.0000
17.000 1.4885 0.07695 0.07106 -0.0539 0.0190 1.0000
17.250 1.4906 0.08000 0.07420 -0.0542 0.0175 1.0000
17.750 1.4914 0.08667 0.08102 -0.0552 0.0146 1.0000
18.000 1.4896 0.09039 0.08480 -0.0559 0.0129 1.0000
18.250 1.4895 0.09396 0.08847 -0.0567 0.0120 1.0000
18.500 1.4872 0.09788 0.09247 -0.0577 0.0109 1.0000
18.750 1.4857 0.10174 0.09642 -0.0587 0.0101 1.0000
19.000 1.4837 0.10570 0.10048 -0.0599 0.0092 1.0000
19.250 1.4802 0.10993 0.10480 -0.0613 0.0085 1.0000
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