EPPLER 431 AIRFOIL (e431-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 431 AIRFOIL (e431-il) Reynolds number: 500,000 Max Cl/Cd: 116.03 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e431-il-500000.txt Download as CSV file: xf-e431-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 431 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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.0389 0.09819 0.09588 -0.1021 0.9427 0.0175
-11.500 -0.0288 0.09342 0.09108 -0.1061 0.9366 0.0181
-11.250 -0.1650 0.10523 0.10290 -0.0881 0.9636 0.0163
-11.000 -0.1505 0.10130 0.09896 -0.0920 0.9578 0.0167
-10.750 -0.0166 0.07522 0.07277 -0.1199 0.9125 0.0194
-10.500 -0.0060 0.07200 0.06947 -0.1219 0.9001 0.0197
-10.250 -0.0005 0.06870 0.06611 -0.1232 0.8879 0.0199
-10.000 0.0025 0.06527 0.06263 -0.1245 0.8775 0.0202
-9.750 0.0026 0.06144 0.05874 -0.1259 0.8683 0.0207
-9.500 -0.0004 0.05730 0.05458 -0.1274 0.8597 0.0209
-9.250 -0.0057 0.05265 0.04989 -0.1295 0.8523 0.0211
-9.000 -0.0174 0.04687 0.04411 -0.1328 0.8449 0.0213
-8.750 -0.0429 0.03966 0.03680 -0.1383 0.8375 0.0210
-8.500 -0.0670 0.03536 0.03240 -0.1394 0.8298 0.0209
-8.250 -0.0886 0.03244 0.02935 -0.1380 0.8223 0.0209
-8.000 -0.1030 0.02984 0.02660 -0.1359 0.8161 0.0212
-7.750 -0.1100 0.02684 0.02344 -0.1342 0.8101 0.0217
-6.500 -0.0949 0.02083 0.01510 -0.1299 0.7956 0.0135
-6.250 -0.0742 0.01800 0.01183 -0.1283 0.7917 0.0113
-6.000 -0.0506 0.01620 0.00965 -0.1274 0.7881 0.0105
-5.750 -0.0265 0.01532 0.00864 -0.1268 0.7844 0.0104
-5.500 -0.0031 0.01455 0.00780 -0.1261 0.7806 0.0104
-5.250 0.0207 0.01387 0.00707 -0.1256 0.7768 0.0107
-5.000 0.0452 0.01331 0.00645 -0.1252 0.7734 0.0111
-4.750 0.0705 0.01284 0.00591 -0.1249 0.7700 0.0119
-4.500 0.0949 0.01244 0.00547 -0.1244 0.7664 0.0126
-4.250 0.1194 0.01193 0.00495 -0.1241 0.7627 0.0144
-4.000 0.1454 0.01155 0.00454 -0.1239 0.7592 0.0176
-3.750 0.1717 0.01112 0.00412 -0.1238 0.7560 0.0311
-3.500 0.1972 0.01066 0.00388 -0.1238 0.7528 0.0790
-3.250 0.2222 0.01018 0.00371 -0.1239 0.7491 0.1498
-3.000 0.2470 0.00945 0.00350 -0.1242 0.7455 0.2962
-2.750 0.2709 0.00818 0.00333 -0.1246 0.7422 0.6069
-2.500 0.2987 0.00823 0.00349 -0.1245 0.7391 0.6882
-2.250 0.3265 0.00834 0.00357 -0.1244 0.7358 0.7133
-2.000 0.3540 0.00845 0.00365 -0.1243 0.7321 0.7300
-1.750 0.3816 0.00858 0.00375 -0.1241 0.7286 0.7437
-1.500 0.4092 0.00872 0.00385 -0.1239 0.7254 0.7541
-1.250 0.4384 0.00888 0.00391 -0.1241 0.7222 0.7634
-1.000 0.4640 0.00896 0.00402 -0.1236 0.7185 0.7698
-0.750 0.4915 0.00908 0.00410 -0.1235 0.7147 0.7793
-0.500 0.5165 0.00926 0.00429 -0.1225 0.7111 0.7890
-0.250 0.5434 0.00941 0.00441 -0.1221 0.7078 0.7981
0.000 0.5691 0.00952 0.00452 -0.1216 0.7040 0.8035
0.250 0.5965 0.00954 0.00452 -0.1217 0.6998 0.8074
0.500 0.6256 0.00955 0.00448 -0.1222 0.6958 0.8106
0.750 0.6542 0.00955 0.00443 -0.1224 0.6922 0.8127
1.000 0.6813 0.00957 0.00444 -0.1224 0.6881 0.8146
1.250 0.7080 0.00957 0.00445 -0.1224 0.6835 0.8166
1.500 0.7357 0.00957 0.00443 -0.1225 0.6792 0.8189
1.750 0.7649 0.00961 0.00442 -0.1230 0.6752 0.8213
2.000 0.7917 0.00962 0.00444 -0.1230 0.6704 0.8237
2.250 0.8195 0.00962 0.00444 -0.1232 0.6653 0.8260
2.500 0.8477 0.00963 0.00441 -0.1235 0.6607 0.8281
2.750 0.8736 0.00964 0.00445 -0.1233 0.6555 0.8301
3.000 0.8995 0.00964 0.00448 -0.1230 0.6499 0.8321
3.250 0.9270 0.00968 0.00448 -0.1231 0.6448 0.8341
3.500 0.9528 0.00970 0.00454 -0.1230 0.6388 0.8365
3.750 0.9790 0.00973 0.00458 -0.1229 0.6326 0.8390
4.000 1.0065 0.00980 0.00462 -0.1230 0.6268 0.8416
4.250 1.0313 0.00981 0.00468 -0.1226 0.6196 0.8440
4.500 1.0567 0.00986 0.00472 -0.1223 0.6129 0.8461
4.750 1.0802 0.00989 0.00482 -0.1216 0.6048 0.8485
5.000 1.1049 0.00998 0.00488 -0.1212 0.5970 0.8510
5.250 1.1285 0.01004 0.00500 -0.1206 0.5879 0.8538
5.500 1.1526 0.01015 0.00510 -0.1201 0.5789 0.8567
5.750 1.1755 0.01025 0.00522 -0.1194 0.5689 0.8595
6.000 1.1966 0.01035 0.00536 -0.1183 0.5583 0.8624
6.250 1.2171 0.01049 0.00551 -0.1170 0.5470 0.8655
6.500 1.2366 0.01067 0.00567 -0.1156 0.5346 0.8688
6.750 1.2552 0.01087 0.00587 -0.1141 0.5204 0.8724
7.000 1.2705 0.01107 0.00607 -0.1119 0.5055 0.8759
7.250 1.2832 0.01131 0.00630 -0.1091 0.4900 0.8798
7.500 1.2950 0.01164 0.00661 -0.1063 0.4724 0.8846
7.750 1.3079 0.01203 0.00697 -0.1038 0.4545 0.8896
8.000 1.3169 0.01244 0.00737 -0.1006 0.4351 0.8948
8.250 1.3258 0.01295 0.00783 -0.0976 0.4156 0.9008
8.750 1.3391 0.01414 0.00896 -0.0909 0.3761 0.9150
9.000 1.3445 0.01481 0.00960 -0.0875 0.3566 0.9245
9.250 1.3475 0.01552 0.01030 -0.0838 0.3379 0.9396
9.500 1.3541 0.01633 0.01109 -0.0812 0.3184 1.0000
9.750 1.3646 0.01734 0.01204 -0.0796 0.2976 1.0000
10.000 1.3735 0.01845 0.01308 -0.0779 0.2778 1.0000
10.250 1.3812 0.01965 0.01421 -0.0760 0.2592 1.0000
10.500 1.3877 0.02094 0.01542 -0.0740 0.2410 1.0000
10.750 1.3949 0.02222 0.01664 -0.0722 0.2228 1.0000
11.000 1.4013 0.02360 0.01796 -0.0704 0.2050 1.0000
11.250 1.4074 0.02503 0.01934 -0.0687 0.1889 1.0000
11.500 1.4137 0.02649 0.02075 -0.0671 0.1741 1.0000
11.750 1.4196 0.02801 0.02223 -0.0655 0.1599 1.0000
12.000 1.4254 0.02959 0.02378 -0.0640 0.1465 1.0000
12.250 1.4309 0.03122 0.02538 -0.0626 0.1339 1.0000
12.500 1.4360 0.03295 0.02709 -0.0612 0.1220 1.0000
12.750 1.4406 0.03476 0.02887 -0.0599 0.1101 1.0000
13.000 1.4448 0.03665 0.03073 -0.0587 0.0996 1.0000
13.250 1.4487 0.03862 0.03268 -0.0575 0.0892 1.0000
13.500 1.4531 0.04062 0.03467 -0.0565 0.0796 1.0000
13.750 1.4574 0.04266 0.03671 -0.0556 0.0711 1.0000
14.000 1.4603 0.04490 0.03896 -0.0547 0.0636 1.0000
14.250 1.4618 0.04734 0.04138 -0.0539 0.0566 1.0000
14.500 1.4662 0.04956 0.04363 -0.0532 0.0506 1.0000
14.750 1.4682 0.05208 0.04620 -0.0526 0.0458 1.0000
15.000 1.4692 0.05477 0.04890 -0.0521 0.0410 1.0000
15.250 1.4720 0.05733 0.05152 -0.0518 0.0372 1.0000
15.500 1.4710 0.06042 0.05463 -0.0515 0.0337 1.0000
15.750 1.4738 0.06313 0.05743 -0.0514 0.0309 1.0000
16.000 1.4726 0.06637 0.06070 -0.0514 0.0282 1.0000
16.250 1.4746 0.06928 0.06370 -0.0515 0.0257 1.0000
16.500 1.4737 0.07264 0.06712 -0.0517 0.0239 1.0000
16.750 1.4716 0.07623 0.07079 -0.0521 0.0220 1.0000
17.000 1.4717 0.07962 0.07427 -0.0526 0.0203 1.0000
17.250 1.4672 0.08370 0.07839 -0.0533 0.0187 1.0000
17.500 1.4672 0.08720 0.08202 -0.0540 0.0175 1.0000
17.750 1.4650 0.09111 0.08602 -0.0549 0.0163 1.0000
18.000 1.4577 0.09588 0.09086 -0.0562 0.0153 1.0000
18.250 1.4561 0.09982 0.09491 -0.0573 0.0143 1.0000
18.500 1.4534 0.10398 0.09919 -0.0587 0.0133 1.0000
18.750 1.4462 0.10894 0.10423 -0.0604 0.0126 1.0000
19.000 1.4380 0.11414 0.10954 -0.0624 0.0119 1.0000
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Polar data table (+)
Polar graphs
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