EPPLER 694 AIRFOIL (e694-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 694 AIRFOIL (e694-il) Reynolds number: 200,000 Max Cl/Cd: 59.43 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e694-il-200000-n5.txt Download as CSV file: xf-e694-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 694 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0774 0.10749 0.10325 -0.1372 0.9291 0.0206
-11.500 -0.0712 0.10497 0.10073 -0.1378 0.9272 0.0200
-11.000 -0.0831 0.09045 0.08625 -0.1450 0.9239 0.0167
-10.750 -0.0767 0.08642 0.08220 -0.1480 0.9229 0.0165
-10.500 -0.0718 0.08159 0.07738 -0.1519 0.9220 0.0164
-10.250 -0.0942 0.07985 0.07571 -0.1470 0.9140 0.0162
-10.000 -0.1018 0.07372 0.06962 -0.1505 0.9112 0.0161
-9.500 -0.1590 0.05733 0.05314 -0.1583 0.8993 0.0153
-9.250 -0.1848 0.05169 0.04730 -0.1606 0.8945 0.0151
-9.000 -0.2229 0.05054 0.04611 -0.1532 0.8839 0.0151
-8.750 -0.2419 0.04648 0.04180 -0.1521 0.8791 0.0150
-8.500 -0.2704 0.04509 0.04028 -0.1450 0.8681 0.0148
-8.250 -0.2748 0.04082 0.03560 -0.1442 0.8645 0.0149
-8.000 -0.2911 0.03917 0.03373 -0.1385 0.8554 0.0148
-7.750 -0.2857 0.03622 0.03037 -0.1371 0.8516 0.0149
-7.500 -0.2696 0.03332 0.02702 -0.1371 0.8498 0.0150
-7.250 -0.2476 0.03094 0.02423 -0.1376 0.8487 0.0152
-7.000 -0.2536 0.03051 0.02363 -0.1323 0.8398 0.0153
-6.750 -0.2312 0.02901 0.02177 -0.1322 0.8377 0.0162
-6.500 -0.2053 0.02772 0.02013 -0.1326 0.8363 0.0167
-6.250 -0.1791 0.02631 0.01857 -0.1330 0.8353 0.0171
-6.000 -0.1515 0.02519 0.01734 -0.1336 0.8345 0.0174
-5.750 -0.1459 0.02512 0.01722 -0.1302 0.8285 0.0177
-5.500 -0.1255 0.02455 0.01656 -0.1295 0.8255 0.0180
-5.250 -0.0991 0.02383 0.01577 -0.1298 0.8238 0.0186
-5.000 -0.0708 0.02315 0.01501 -0.1304 0.8226 0.0193
-4.750 -0.0414 0.02252 0.01430 -0.1313 0.8217 0.0201
-4.250 0.0202 0.02140 0.01305 -0.1336 0.8203 0.0232
-4.000 0.0258 0.02190 0.01352 -0.1303 0.8133 0.0248
-3.750 0.0535 0.02161 0.01318 -0.1309 0.8116 0.0276
-3.500 0.0835 0.02126 0.01280 -0.1318 0.8103 0.0327
-3.250 0.1155 0.02079 0.01240 -0.1332 0.8093 0.0513
-3.000 0.1486 0.02029 0.01209 -0.1349 0.8085 0.0987
-2.750 0.1836 0.01962 0.01182 -0.1374 0.8078 0.1916
-2.500 0.2226 0.01870 0.01162 -0.1411 0.8074 0.3747
-2.000 0.2618 0.01881 0.01268 -0.1393 0.7998 0.6169
-1.750 0.2811 0.01898 0.01303 -0.1372 0.7977 0.6777
-1.500 0.3072 0.01910 0.01312 -0.1366 0.7964 0.7157
-1.250 0.3352 0.01916 0.01312 -0.1365 0.7953 0.7374
-1.000 0.3642 0.01920 0.01308 -0.1365 0.7945 0.7571
-0.750 0.3729 0.02006 0.01393 -0.1332 0.7889 0.7720
-0.500 0.3919 0.02041 0.01424 -0.1314 0.7857 0.7851
-0.250 0.4212 0.02045 0.01421 -0.1318 0.7841 0.7950
0.000 0.4471 0.02039 0.01411 -0.1313 0.7828 0.8001
0.250 0.4779 0.02025 0.01391 -0.1318 0.7818 0.8066
0.500 0.5089 0.02007 0.01368 -0.1324 0.7810 0.8128
0.750 0.5384 0.01985 0.01343 -0.1324 0.7802 0.8191
1.750 0.6351 0.02035 0.01386 -0.1308 0.7675 0.8382
2.000 0.6715 0.02005 0.01354 -0.1326 0.7666 0.8416
2.250 0.7055 0.01966 0.01314 -0.1337 0.7658 0.8440
2.500 0.7428 0.01922 0.01269 -0.1355 0.7650 0.8465
3.000 0.7771 0.02003 0.01354 -0.1325 0.7529 0.8537
3.250 0.8161 0.01963 0.01315 -0.1348 0.7517 0.8563
3.500 0.8550 0.01908 0.01262 -0.1367 0.7504 0.8582
4.000 0.8920 0.01950 0.01312 -0.1338 0.7376 0.8647
4.250 0.9342 0.01892 0.01256 -0.1365 0.7355 0.8673
4.500 0.9806 0.01831 0.01198 -0.1400 0.7335 0.8694
4.750 0.9725 0.01937 0.01312 -0.1340 0.7218 0.8731
5.000 1.0112 0.01890 0.01269 -0.1360 0.7189 0.8748
5.500 1.0441 0.01948 0.01341 -0.1326 0.7029 0.8799
5.750 1.0421 0.02055 0.01457 -0.1280 0.6897 0.8831
6.250 1.0610 0.02190 0.01607 -0.1228 0.6659 0.8875
6.500 1.0849 0.02183 0.01607 -0.1223 0.6559 0.8896
6.750 1.1110 0.02164 0.01592 -0.1221 0.6427 0.8916
7.000 1.1405 0.02133 0.01562 -0.1224 0.6269 0.8933
7.250 1.1732 0.02094 0.01522 -0.1232 0.6085 0.8949
7.500 1.2066 0.02059 0.01480 -0.1242 0.5857 0.8963
7.750 1.2314 0.02072 0.01483 -0.1239 0.5577 0.8980
8.000 1.2497 0.02115 0.01514 -0.1226 0.5283 0.8999
8.250 1.2619 0.02181 0.01571 -0.1203 0.4992 0.9022
8.500 1.2692 0.02276 0.01652 -0.1174 0.4673 0.9047
8.750 1.2734 0.02395 0.01756 -0.1142 0.4326 0.9070
9.000 1.2736 0.02544 0.01886 -0.1106 0.3945 0.9093
9.250 1.2740 0.02706 0.02028 -0.1073 0.3556 0.9116
9.500 1.2726 0.02883 0.02185 -0.1039 0.3161 0.9139
9.750 1.2724 0.03058 0.02343 -0.1008 0.2770 0.9161
10.000 1.2744 0.03230 0.02499 -0.0981 0.2467 0.9188
10.250 1.2802 0.03387 0.02647 -0.0961 0.2218 0.9217
10.500 1.2872 0.03545 0.02796 -0.0943 0.1952 0.9246
10.750 1.2922 0.03718 0.02956 -0.0924 0.1657 0.9272
11.000 1.2959 0.03902 0.03125 -0.0903 0.1369 0.9299
11.250 1.3007 0.04087 0.03299 -0.0886 0.1112 0.9328
11.500 1.3052 0.04282 0.03481 -0.0869 0.0861 0.9359
12.000 1.3171 0.04652 0.03840 -0.0839 0.0515 0.9434
12.250 1.3210 0.04860 0.04042 -0.0823 0.0366 0.9485
12.500 1.3252 0.05061 0.04244 -0.0808 0.0274 0.9560
12.750 1.3287 0.05260 0.04447 -0.0793 0.0217 0.9776
13.000 1.3355 0.05474 0.04670 -0.0784 0.0187 1.0000
13.250 1.3428 0.05696 0.04901 -0.0777 0.0170 1.0000
13.500 1.3501 0.05924 0.05139 -0.0771 0.0156 1.0000
13.750 1.3554 0.06176 0.05400 -0.0765 0.0146 1.0000
14.000 1.3608 0.06430 0.05667 -0.0760 0.0138 1.0000
14.250 1.3660 0.06691 0.05942 -0.0755 0.0134 1.0000
14.500 1.3697 0.06974 0.06238 -0.0751 0.0129 1.0000
14.750 1.3728 0.07271 0.06550 -0.0748 0.0125 1.0000
15.000 1.3748 0.07586 0.06878 -0.0747 0.0122 1.0000
15.250 1.3759 0.07918 0.07224 -0.0746 0.0119 1.0000
15.500 1.3759 0.08269 0.07588 -0.0746 0.0117 1.0000
15.750 1.3746 0.08643 0.07973 -0.0748 0.0115 1.0000
16.000 1.3724 0.09036 0.08378 -0.0752 0.0113 1.0000
16.250 1.3708 0.09426 0.08779 -0.0757 0.0111 1.0000
16.500 1.3712 0.09793 0.09161 -0.0763 0.0110 1.0000
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