EPPLER 338 AIRFOIL (e338-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 338 AIRFOIL (e338-il) Reynolds number: 500,000 Max Cl/Cd: 88.59 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e338-il-500000-n5.txt Download as CSV file: xf-e338-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 338 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2163 0.08653 0.08348 -0.0412 0.7083 0.0104
-9.750 -0.2169 0.08229 0.07920 -0.0426 0.6939 0.0104
-9.500 -0.2174 0.07818 0.07504 -0.0440 0.6812 0.0104
-9.250 -0.2187 0.07400 0.07082 -0.0455 0.6699 0.0104
-9.000 -0.2212 0.06960 0.06640 -0.0473 0.6593 0.0104
-8.500 -0.2928 0.06951 0.06620 -0.0599 0.6780 0.0104
-8.000 -0.3159 0.06270 0.05920 -0.0581 0.6543 0.0104
-7.500 -0.3280 0.05567 0.05196 -0.0550 0.6332 0.0078
-7.000 -0.3230 0.05033 0.04636 -0.0522 0.6120 0.0073
-6.750 -0.3171 0.04741 0.04327 -0.0506 0.6025 0.0071
-6.250 -0.3251 0.03323 0.02824 -0.0418 0.5902 0.0056
-6.000 -0.3158 0.02946 0.02413 -0.0389 0.5817 0.0056
-5.750 -0.3096 0.02379 0.01782 -0.0347 0.5746 0.0055
-5.500 -0.2948 0.01939 0.01263 -0.0316 0.5670 0.0057
-5.250 -0.2727 0.01781 0.01072 -0.0305 0.5578 0.0058
-5.000 -0.2487 0.01708 0.00986 -0.0298 0.5489 0.0061
-4.750 -0.2242 0.01646 0.00908 -0.0291 0.5398 0.0063
-4.500 -0.1991 0.01575 0.00822 -0.0285 0.5309 0.0065
-4.250 -0.1741 0.01511 0.00742 -0.0278 0.5221 0.0068
-4.000 -0.1491 0.01448 0.00666 -0.0271 0.5135 0.0070
-3.750 -0.1242 0.01400 0.00606 -0.0264 0.5061 0.0074
-3.500 -0.0993 0.01356 0.00553 -0.0257 0.4988 0.0076
-3.000 -0.0498 0.01290 0.00475 -0.0244 0.4844 0.0087
-2.750 -0.0251 0.01264 0.00443 -0.0237 0.4772 0.0093
-2.500 -0.0002 0.01236 0.00409 -0.0230 0.4708 0.0098
-2.250 0.0245 0.01209 0.00375 -0.0223 0.4642 0.0103
-2.000 0.0489 0.01182 0.00344 -0.0215 0.4586 0.0111
-1.750 0.0743 0.01162 0.00321 -0.0210 0.4527 0.0124
-1.500 0.0994 0.01145 0.00299 -0.0203 0.4465 0.0146
-1.250 0.1247 0.01130 0.00282 -0.0197 0.4412 0.0194
-1.000 0.1500 0.01114 0.00269 -0.0192 0.4356 0.0314
-0.750 0.1745 0.01095 0.00259 -0.0186 0.4305 0.0635
-0.500 0.1985 0.01071 0.00252 -0.0179 0.4262 0.1210
-0.250 0.2002 0.00890 0.00228 -0.0135 0.4226 0.5889
0.000 0.2062 0.00845 0.00283 -0.0078 0.4186 0.8778
0.250 0.2291 0.00874 0.00306 -0.0062 0.4136 0.8984
0.500 0.2536 0.00901 0.00328 -0.0050 0.4095 0.9107
0.750 0.2767 0.00920 0.00341 -0.0036 0.4054 0.9207
1.000 0.3069 0.00952 0.00368 -0.0035 0.4010 0.9290
1.250 0.3285 0.00964 0.00372 -0.0020 0.3970 0.9354
1.500 0.3566 0.00967 0.00370 -0.0021 0.3931 0.9363
1.750 0.3844 0.00971 0.00369 -0.0021 0.3890 0.9372
2.000 0.4114 0.00975 0.00368 -0.0020 0.3854 0.9381
2.250 0.4381 0.00982 0.00368 -0.0018 0.3816 0.9391
2.500 0.4651 0.00987 0.00370 -0.0017 0.3782 0.9402
2.750 0.4916 0.00991 0.00371 -0.0015 0.3745 0.9412
3.000 0.5177 0.00996 0.00373 -0.0013 0.3710 0.9423
3.250 0.5431 0.01002 0.00375 -0.0009 0.3675 0.9435
3.500 0.5684 0.01009 0.00379 -0.0005 0.3642 0.9450
3.750 0.5939 0.01013 0.00383 -0.0001 0.3610 0.9462
4.000 0.6190 0.01018 0.00387 0.0003 0.3576 0.9474
4.250 0.6437 0.01025 0.00392 0.0007 0.3543 0.9486
4.500 0.6688 0.01035 0.00398 0.0011 0.3508 0.9496
4.750 0.6959 0.01042 0.00406 0.0011 0.3478 0.9502
5.000 0.7229 0.01049 0.00415 0.0010 0.3444 0.9510
5.250 0.7496 0.01058 0.00424 0.0011 0.3406 0.9520
5.500 0.7756 0.01070 0.00436 0.0012 0.3373 0.9530
5.750 0.8015 0.01081 0.00447 0.0014 0.3338 0.9540
6.000 0.8279 0.01089 0.00458 0.0015 0.3302 0.9550
6.250 0.8536 0.01100 0.00470 0.0016 0.3263 0.9560
6.500 0.8786 0.01112 0.00483 0.0019 0.3226 0.9572
6.750 0.9033 0.01125 0.00497 0.0023 0.3189 0.9585
7.000 0.9286 0.01135 0.00511 0.0025 0.3150 0.9598
7.250 0.9528 0.01147 0.00526 0.0029 0.3096 0.9611
7.500 0.9760 0.01162 0.00541 0.0035 0.3034 0.9626
7.750 1.0019 0.01176 0.00557 0.0036 0.2961 0.9637
8.000 1.0268 0.01195 0.00576 0.0038 0.2893 0.9650
8.250 1.0525 0.01210 0.00597 0.0038 0.2839 0.9663
8.500 1.0771 0.01230 0.00619 0.0040 0.2784 0.9676
8.750 1.1016 0.01250 0.00642 0.0042 0.2720 0.9691
9.000 1.1250 0.01273 0.00667 0.0046 0.2645 0.9709
9.250 1.1481 0.01296 0.00693 0.0051 0.2581 0.9728
9.500 1.1698 0.01323 0.00722 0.0057 0.2499 0.9749
9.750 1.1950 0.01354 0.00755 0.0055 0.2405 0.9762
10.000 1.2191 0.01391 0.00793 0.0055 0.2312 0.9778
10.500 1.2646 0.01474 0.00879 0.0058 0.2110 0.9822
10.750 1.2847 0.01520 0.00927 0.0064 0.2018 0.9853
11.000 1.3067 0.01581 0.00988 0.0063 0.1888 0.9876
11.250 1.3275 0.01648 0.01054 0.0064 0.1772 0.9910
11.500 1.3457 0.01724 0.01129 0.0067 0.1647 0.9968
11.750 1.3525 0.01793 0.01199 0.0092 0.1551 1.0000
12.000 1.3562 0.01865 0.01273 0.0122 0.1471 1.0000
12.250 1.3595 0.01964 0.01373 0.0147 0.1380 1.0000
12.500 1.3604 0.02093 0.01500 0.0170 0.1275 1.0000
12.750 1.3608 0.02245 0.01652 0.0188 0.1172 1.0000
13.000 1.3602 0.02423 0.01831 0.0203 0.1075 1.0000
13.250 1.3596 0.02622 0.02032 0.0213 0.1002 1.0000
13.500 1.3571 0.02853 0.02267 0.0221 0.0934 1.0000
13.750 1.3554 0.03093 0.02511 0.0225 0.0870 1.0000
14.000 1.3483 0.03396 0.02817 0.0228 0.0798 1.0000
14.250 1.3459 0.03665 0.03094 0.0229 0.0744 1.0000
14.500 1.3338 0.04039 0.03469 0.0228 0.0657 1.0000
14.750 1.3229 0.04411 0.03844 0.0225 0.0599 1.0000
15.000 1.3147 0.04764 0.04203 0.0222 0.0564 1.0000
15.250 1.3029 0.05163 0.04606 0.0217 0.0527 1.0000
15.500 1.2969 0.05511 0.04962 0.0211 0.0510 1.0000
15.750 1.2902 0.05876 0.05335 0.0203 0.0492 1.0000
16.000 1.2819 0.06271 0.05737 0.0194 0.0473 1.0000
16.250 1.2747 0.06661 0.06135 0.0184 0.0460 1.0000
16.500 1.2666 0.07072 0.06552 0.0173 0.0442 1.0000
16.750 1.2626 0.07435 0.06924 0.0163 0.0427 1.0000
17.000 1.2587 0.07804 0.07303 0.0151 0.0415 1.0000
17.250 1.2539 0.08190 0.07697 0.0139 0.0401 1.0000
17.500 1.2473 0.08609 0.08122 0.0125 0.0386 1.0000
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