EPPLER 338 AIRFOIL (e338-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 338 AIRFOIL (e338-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.05 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e338-il-1000000.txt Download as CSV file: xf-e338-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3487 0.10563 0.10402 -0.0236 1.0000 0.0080
-10.250 -0.3461 0.10236 0.10078 -0.0245 1.0000 0.0081
-10.000 -0.3441 0.09866 0.09710 -0.0260 1.0000 0.0080
-9.750 -0.3410 0.09581 0.09426 -0.0265 1.0000 0.0082
-9.500 -0.3399 0.09186 0.09034 -0.0284 0.9997 0.0081
-9.250 -0.2966 0.08478 0.08319 -0.0422 0.9368 0.0083
-9.000 -0.2572 0.07763 0.07551 -0.0567 0.8180 0.0084
-8.750 -0.2634 0.07443 0.07212 -0.0577 0.7670 0.0085
-8.500 -0.2768 0.06983 0.06742 -0.0610 0.7408 0.0085
-8.250 -0.2901 0.06623 0.06372 -0.0616 0.7189 0.0085
-8.000 -0.3049 0.06318 0.06058 -0.0599 0.6998 0.0085
-7.750 -0.3113 0.06034 0.05763 -0.0586 0.6841 0.0086
-7.500 -0.3143 0.05704 0.05421 -0.0576 0.6699 0.0086
-7.250 -0.3140 0.05388 0.05093 -0.0563 0.6565 0.0086
-7.000 -0.3110 0.05081 0.04773 -0.0548 0.6444 0.0088
-6.750 -0.3055 0.04783 0.04460 -0.0533 0.6327 0.0089
-6.250 -0.2904 0.04154 0.03795 -0.0493 0.6111 0.0095
-6.000 -0.2800 0.03835 0.03456 -0.0471 0.6012 0.0098
-5.750 -0.2661 0.03338 0.02921 -0.0435 0.5922 0.0103
-5.500 -0.2652 0.02808 0.02349 -0.0393 0.5852 0.0106
-5.250 -0.2413 0.01270 0.00829 -0.0364 0.5634 0.0108
-5.000 -0.2242 0.01145 0.00690 -0.0351 0.5544 0.0110
-4.750 -0.2059 0.01016 0.00544 -0.0338 0.5457 0.0113
-4.500 -0.1974 0.01712 0.01107 -0.0297 0.5503 0.0080
-4.250 -0.1748 0.01484 0.00854 -0.0285 0.5412 0.0074
-4.000 -0.1495 0.01350 0.00697 -0.0276 0.5323 0.0072
-3.750 -0.1242 0.01275 0.00604 -0.0268 0.5231 0.0076
-3.500 -0.0978 0.01245 0.00563 -0.0264 0.5146 0.0079
-3.250 -0.0751 0.01150 0.00458 -0.0253 0.5067 0.0084
-3.000 -0.0496 0.01120 0.00426 -0.0247 0.4990 0.0090
-2.750 -0.0249 0.01091 0.00389 -0.0240 0.4911 0.0093
-2.500 0.0006 0.01064 0.00358 -0.0234 0.4839 0.0097
-2.250 0.0254 0.01041 0.00327 -0.0227 0.4763 0.0101
-2.000 0.0511 0.01019 0.00302 -0.0221 0.4697 0.0104
-1.750 0.0754 0.00988 0.00266 -0.0213 0.4631 0.0114
-1.500 0.1015 0.00977 0.00253 -0.0209 0.4570 0.0130
-1.250 0.1269 0.00956 0.00229 -0.0203 0.4509 0.0158
-1.000 0.1520 0.00939 0.00211 -0.0196 0.4446 0.0251
-0.750 0.1767 0.00912 0.00201 -0.0190 0.4393 0.0711
-0.500 0.1997 0.00876 0.00194 -0.0181 0.4339 0.1697
-0.250 0.1929 0.00658 0.00167 -0.0119 0.4302 0.7439
0.000 0.2101 0.00659 0.00206 -0.0089 0.4258 0.8825
0.250 0.2343 0.00684 0.00230 -0.0076 0.4210 0.9014
0.500 0.2569 0.00718 0.00261 -0.0058 0.4160 0.9149
0.750 0.2800 0.00744 0.00283 -0.0043 0.4113 0.9238
1.000 0.3049 0.00765 0.00302 -0.0032 0.4076 0.9306
1.250 0.3291 0.00781 0.00314 -0.0021 0.4034 0.9368
1.500 0.3587 0.00810 0.00337 -0.0019 0.3987 0.9422
1.750 0.3857 0.00822 0.00346 -0.0016 0.3948 0.9460
2.000 0.4101 0.00821 0.00343 -0.0009 0.3914 0.9477
2.250 0.4345 0.00823 0.00340 -0.0004 0.3876 0.9491
2.500 0.4605 0.00824 0.00336 0.0000 0.3836 0.9501
2.750 0.4870 0.00826 0.00335 0.0001 0.3798 0.9508
3.000 0.5146 0.00826 0.00334 0.0001 0.3768 0.9516
3.250 0.5419 0.00829 0.00335 0.0002 0.3733 0.9524
3.500 0.5686 0.00834 0.00337 0.0003 0.3696 0.9532
3.750 0.5943 0.00843 0.00341 0.0005 0.3654 0.9541
4.000 0.6215 0.00844 0.00343 0.0006 0.3629 0.9549
4.250 0.6484 0.00846 0.00345 0.0006 0.3598 0.9559
4.500 0.6745 0.00851 0.00349 0.0008 0.3565 0.9570
4.750 0.7000 0.00859 0.00354 0.0011 0.3527 0.9580
5.000 0.7254 0.00866 0.00360 0.0014 0.3492 0.9590
5.250 0.7519 0.00868 0.00364 0.0015 0.3464 0.9599
5.500 0.7781 0.00873 0.00369 0.0017 0.3428 0.9608
5.750 0.8038 0.00880 0.00375 0.0019 0.3394 0.9617
6.000 0.8285 0.00894 0.00385 0.0022 0.3348 0.9626
6.250 0.8557 0.00893 0.00389 0.0022 0.3316 0.9635
6.500 0.8825 0.00898 0.00395 0.0021 0.3268 0.9644
6.750 0.9083 0.00910 0.00404 0.0023 0.3216 0.9652
7.000 0.9351 0.00916 0.00413 0.0022 0.3170 0.9661
7.250 0.9616 0.00924 0.00423 0.0022 0.3125 0.9670
7.500 0.9872 0.00936 0.00434 0.0024 0.3081 0.9680
7.750 1.0126 0.00948 0.00448 0.0026 0.3042 0.9691
8.000 1.0388 0.00956 0.00459 0.0026 0.3001 0.9702
8.250 1.0636 0.00968 0.00472 0.0028 0.2941 0.9715
8.500 1.0880 0.00982 0.00487 0.0032 0.2891 0.9728
8.750 1.1127 0.00993 0.00500 0.0035 0.2833 0.9741
9.000 1.1367 0.01011 0.00518 0.0038 0.2771 0.9755
9.250 1.1632 0.01025 0.00535 0.0036 0.2708 0.9768
9.500 1.1885 0.01047 0.00557 0.0037 0.2636 0.9782
9.750 1.2146 0.01065 0.00578 0.0035 0.2568 0.9795
10.000 1.2390 0.01093 0.00605 0.0036 0.2486 0.9811
10.250 1.2641 0.01116 0.00630 0.0036 0.2402 0.9827
10.500 1.2869 0.01146 0.00660 0.0039 0.2308 0.9848
10.750 1.3118 0.01186 0.00697 0.0037 0.2186 0.9862
11.000 1.3377 0.01232 0.00740 0.0032 0.2058 0.9874
11.250 1.3627 0.01284 0.00789 0.0027 0.1919 0.9887
11.500 1.3855 0.01346 0.00845 0.0026 0.1757 0.9905
11.750 1.4055 0.01420 0.00912 0.0028 0.1580 0.9929
12.000 1.4232 0.01509 0.00992 0.0031 0.1402 0.9963
12.250 1.4423 0.01593 0.01072 0.0031 0.1257 1.0000
12.500 1.4334 0.01643 0.01121 0.0089 0.1188 1.0000
12.750 1.4372 0.01728 0.01205 0.0117 0.1093 1.0000
13.000 1.4388 0.01841 0.01315 0.0142 0.0988 1.0000
13.250 1.4400 0.01972 0.01445 0.0164 0.0900 1.0000
13.500 1.4393 0.02131 0.01604 0.0184 0.0816 1.0000
13.750 1.4322 0.02357 0.01825 0.0201 0.0685 1.0000
14.000 1.4271 0.02597 0.02065 0.0212 0.0600 1.0000
14.250 1.4157 0.02913 0.02379 0.0221 0.0516 1.0000
14.500 1.4107 0.03194 0.02664 0.0224 0.0483 1.0000
14.750 1.4146 0.03399 0.02879 0.0225 0.0486 1.0000
15.000 1.4119 0.03674 0.03162 0.0225 0.0475 1.0000
15.250 1.4016 0.04031 0.03524 0.0225 0.0443 1.0000
15.500 1.3990 0.04315 0.03816 0.0223 0.0426 1.0000
15.750 1.3947 0.04623 0.04134 0.0220 0.0417 1.0000
16.000 1.3842 0.05004 0.04520 0.0215 0.0394 1.0000
16.250 1.3778 0.05353 0.04877 0.0210 0.0388 1.0000
16.500 1.3671 0.05761 0.05290 0.0202 0.0367 1.0000
16.750 1.3629 0.06100 0.05638 0.0194 0.0358 1.0000
17.000 1.3600 0.06430 0.05976 0.0186 0.0345 1.0000
17.250 1.3542 0.06803 0.06357 0.0176 0.0333 1.0000
17.500 1.3484 0.07179 0.06740 0.0166 0.0323 1.0000
17.750 1.3384 0.07619 0.07184 0.0153 0.0302 1.0000
18.000 1.3338 0.07996 0.07567 0.0141 0.0284 1.0000
18.250 1.3276 0.08397 0.07974 0.0127 0.0267 1.0000
18.500 1.3189 0.08842 0.08422 0.0112 0.0246 1.0000
18.750 1.3136 0.09246 0.08834 0.0097 0.0233 1.0000
19.000 1.3055 0.09698 0.09290 0.0080 0.0213 1.0000
19.250 1.2977 0.10147 0.09744 0.0062 0.0196 1.0000
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