EPPLER 664 AIRFOIL (e664-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 664 AIRFOIL (e664-il) Reynolds number: 100,000 Max Cl/Cd: 33.22 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e664-il-100000-n5.txt Download as CSV file: xf-e664-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 664 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3396 0.09710 0.09217 -0.0849 0.9604 0.0279
-11.750 -0.3428 0.08920 0.08425 -0.0909 0.9537 0.0275
-11.500 -0.3593 0.07752 0.07249 -0.1008 0.9472 0.0269
-11.250 -0.3808 0.06884 0.06362 -0.1084 0.9390 0.0263
-11.000 -0.4033 0.06187 0.05637 -0.1132 0.9312 0.0260
-10.750 -0.4201 0.05700 0.05120 -0.1149 0.9222 0.0258
-10.500 -0.4334 0.05265 0.04650 -0.1154 0.9146 0.0258
-10.250 -0.4450 0.04951 0.04305 -0.1139 0.9054 0.0256
-10.000 -0.4529 0.04647 0.03964 -0.1119 0.8982 0.0256
-9.750 -0.4608 0.04429 0.03715 -0.1085 0.8900 0.0255
-9.500 -0.4593 0.04186 0.03435 -0.1064 0.8841 0.0256
-9.250 -0.4521 0.03951 0.03160 -0.1047 0.8797 0.0258
-9.000 -0.4459 0.03770 0.02948 -0.1022 0.8741 0.0260
-8.750 -0.4321 0.03580 0.02725 -0.1008 0.8700 0.0263
-8.500 -0.4121 0.03391 0.02504 -0.1002 0.8669 0.0268
-8.250 -0.3867 0.03213 0.02294 -0.1003 0.8646 0.0274
-8.000 -0.3673 0.03092 0.02144 -0.0992 0.8604 0.0283
-7.750 -0.3478 0.02996 0.02047 -0.0984 0.8564 0.0296
-7.500 -0.3254 0.02907 0.01951 -0.0980 0.8532 0.0312
-7.250 -0.2995 0.02808 0.01837 -0.0980 0.8509 0.0330
-7.000 -0.2730 0.02707 0.01721 -0.0979 0.8489 0.0345
-6.750 -0.2568 0.02639 0.01655 -0.0965 0.8457 0.0360
-6.500 -0.2448 0.02595 0.01608 -0.0941 0.8414 0.0380
-6.250 -0.2290 0.02542 0.01546 -0.0923 0.8378 0.0410
-6.000 -0.2115 0.02485 0.01489 -0.0910 0.8349 0.0458
-5.750 -0.1925 0.02424 0.01426 -0.0898 0.8326 0.0540
-5.500 -0.1789 0.02379 0.01386 -0.0877 0.8297 0.0670
-5.250 -0.1720 0.02363 0.01378 -0.0844 0.8250 0.0855
-5.000 -0.1585 0.02321 0.01358 -0.0822 0.8215 0.1219
-4.750 -0.1436 0.02256 0.01340 -0.0805 0.8187 0.1994
-4.500 -0.1371 0.02163 0.01322 -0.0774 0.8163 0.3337
-4.250 -0.0627 0.02336 0.01646 -0.0797 0.8172 0.6450
-4.000 -0.0661 0.02374 0.01674 -0.0741 0.8134 0.6841
-3.750 -0.0873 0.02417 0.01717 -0.0659 0.8064 0.7083
-3.500 -0.0771 0.02470 0.01756 -0.0625 0.8029 0.7339
-3.250 -0.0628 0.02509 0.01777 -0.0599 0.8003 0.7559
-3.000 -0.0328 0.02574 0.01825 -0.0593 0.7988 0.7723
-2.750 -0.0453 0.02659 0.01909 -0.0520 0.7914 0.7843
-2.500 -0.0223 0.02735 0.01974 -0.0501 0.7883 0.8001
-2.250 0.0056 0.02802 0.02029 -0.0489 0.7861 0.8174
-2.000 0.0605 0.02853 0.02063 -0.0527 0.7854 0.8284
-1.750 0.0951 0.02858 0.02054 -0.0537 0.7838 0.8365
-1.500 0.1320 0.02849 0.02031 -0.0555 0.7824 0.8417
-1.250 0.0993 0.02921 0.02109 -0.0450 0.7729 0.8513
-1.000 0.1258 0.02915 0.02093 -0.0451 0.7701 0.8548
-0.750 0.1465 0.02899 0.02067 -0.0441 0.7677 0.8593
-0.500 0.1272 0.02944 0.02114 -0.0362 0.7598 0.8658
-0.250 0.1420 0.02950 0.02114 -0.0343 0.7553 0.8692
0.000 0.1652 0.02934 0.02090 -0.0338 0.7527 0.8721
0.250 0.1891 0.02909 0.02057 -0.0335 0.7506 0.8751
0.750 0.1816 0.02950 0.02094 -0.0233 0.7367 0.8828
1.000 0.2135 0.02923 0.02061 -0.0243 0.7348 0.8840
1.250 0.2473 0.02897 0.02029 -0.0256 0.7331 0.8854
1.750 0.2420 0.02921 0.02050 -0.0162 0.7185 0.8925
2.250 0.2615 0.02970 0.02099 -0.0114 0.7046 0.8968
2.500 0.2947 0.02936 0.02061 -0.0124 0.7026 0.8974
2.750 0.3307 0.02895 0.02018 -0.0139 0.7012 0.8981
3.000 0.3173 0.02981 0.02108 -0.0084 0.6884 0.9021
3.250 0.3516 0.02939 0.02064 -0.0095 0.6865 0.9029
3.750 0.3811 0.02979 0.02107 -0.0068 0.6721 0.9062
4.000 0.4168 0.02930 0.02059 -0.0080 0.6704 0.9067
4.500 0.4511 0.02958 0.02095 -0.0057 0.6557 0.9100
5.000 0.4897 0.02978 0.02124 -0.0042 0.6412 0.9129
5.500 0.5317 0.02984 0.02141 -0.0031 0.6265 0.9155
6.000 0.5764 0.02976 0.02146 -0.0024 0.6117 0.9183
6.500 0.6235 0.02952 0.02137 -0.0018 0.5964 0.9213
6.750 0.6387 0.02986 0.02179 -0.0007 0.5850 0.9228
7.000 0.6735 0.02908 0.02110 -0.0014 0.5805 0.9236
7.250 0.6901 0.02939 0.02150 -0.0005 0.5683 0.9252
7.500 0.7142 0.02928 0.02146 -0.0002 0.5581 0.9265
7.750 0.7481 0.02854 0.02082 -0.0008 0.5501 0.9275
8.000 0.7701 0.02858 0.02094 -0.0004 0.5368 0.9289
8.250 0.7959 0.02840 0.02083 -0.0003 0.5235 0.9305
8.500 0.8239 0.02810 0.02060 -0.0003 0.5092 0.9321
8.750 0.8513 0.02786 0.02041 -0.0003 0.4931 0.9338
9.000 0.8771 0.02772 0.02029 -0.0001 0.4750 0.9354
9.250 0.9031 0.02759 0.02016 0.0001 0.4553 0.9370
9.500 0.9214 0.02797 0.02055 0.0008 0.4335 0.9388
9.750 0.9407 0.02832 0.02086 0.0015 0.4108 0.9406
10.000 0.9568 0.02891 0.02144 0.0024 0.3882 0.9427
10.250 0.9702 0.02971 0.02221 0.0033 0.3650 0.9449
10.500 0.9829 0.03059 0.02305 0.0043 0.3428 0.9473
10.750 0.9936 0.03162 0.02408 0.0053 0.3203 0.9498
11.000 1.0033 0.03274 0.02515 0.0063 0.2988 0.9528
11.250 1.0125 0.03398 0.02640 0.0073 0.2773 0.9564
11.500 1.0210 0.03534 0.02775 0.0080 0.2564 0.9604
11.750 1.0295 0.03681 0.02920 0.0086 0.2367 0.9648
12.000 1.0383 0.03835 0.03076 0.0090 0.2174 0.9701
12.250 1.0457 0.03993 0.03236 0.0094 0.1994 0.9789
12.500 1.0514 0.04152 0.03396 0.0100 0.1834 1.0000
12.750 1.0579 0.04341 0.03587 0.0103 0.1677 1.0000
13.000 1.0631 0.04547 0.03792 0.0106 0.1519 1.0000
13.250 1.0667 0.04774 0.04016 0.0108 0.1360 1.0000
13.500 1.0691 0.05023 0.04260 0.0109 0.1203 1.0000
13.750 1.0715 0.05279 0.04513 0.0108 0.1060 1.0000
14.000 1.0742 0.05542 0.04776 0.0106 0.0921 1.0000
14.250 1.0772 0.05811 0.05050 0.0103 0.0819 1.0000
14.500 1.0807 0.06082 0.05329 0.0099 0.0726 1.0000
14.750 1.0825 0.06378 0.05632 0.0095 0.0647 1.0000
15.000 1.0816 0.06714 0.05970 0.0089 0.0582 1.0000
15.250 1.0815 0.07053 0.06319 0.0081 0.0513 1.0000
15.500 1.0802 0.07415 0.06689 0.0073 0.0457 1.0000
15.750 1.0764 0.07818 0.07098 0.0062 0.0418 1.0000
16.000 1.0745 0.08206 0.07499 0.0050 0.0384 1.0000
16.250 1.0713 0.08621 0.07925 0.0037 0.0357 1.0000
16.500 1.0659 0.09074 0.08384 0.0021 0.0340 1.0000
16.750 1.0648 0.09471 0.08799 0.0007 0.0319 1.0000
17.000 1.0631 0.09884 0.09225 -0.0009 0.0303 1.0000
17.250 1.0603 0.10322 0.09672 -0.0029 0.0289 1.0000
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