EPPLER 342 AIRFOIL (e342-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 342 AIRFOIL (e342-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.28 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e342-il-1000000.txt Download as CSV file: xf-e342-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 342 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3130 0.08186 0.07955 -0.0481 0.7689 0.0110
-9.500 -0.3208 0.07714 0.07473 -0.0507 0.7385 0.0110
-9.250 -0.3301 0.07281 0.07032 -0.0541 0.7143 0.0109
-9.000 -0.3588 0.06546 0.06286 -0.0572 0.7017 0.0111
-8.750 -0.3644 0.06414 0.06146 -0.0557 0.6820 0.0109
-8.500 -0.3868 0.05954 0.05672 -0.0531 0.6698 0.0111
-8.250 -0.4001 0.05643 0.05349 -0.0497 0.6570 0.0111
-7.500 -0.4123 0.04406 0.04050 -0.0405 0.6250 0.0113
-7.250 -0.4239 0.03964 0.03585 -0.0363 0.6162 0.0115
-7.000 -0.4162 0.03798 0.03407 -0.0341 0.6044 0.0116
-6.750 -0.4062 0.03612 0.03205 -0.0320 0.5930 0.0117
-6.500 -0.3945 0.03441 0.03017 -0.0298 0.5822 0.0118
-6.250 -0.3815 0.03264 0.02825 -0.0278 0.5718 0.0120
-6.000 -0.3677 0.03072 0.02613 -0.0256 0.5625 0.0123
-5.750 -0.3529 0.02864 0.02384 -0.0233 0.5534 0.0127
-4.750 -0.2796 0.01595 0.00942 -0.0130 0.5221 0.0086
-4.500 -0.2534 0.01435 0.00761 -0.0125 0.5132 0.0082
-4.250 -0.2274 0.01343 0.00657 -0.0119 0.5047 0.0079
-4.000 -0.2028 0.01269 0.00570 -0.0110 0.4959 0.0078
-3.750 -0.1783 0.01218 0.00512 -0.0102 0.4886 0.0077
-3.500 -0.1544 0.01177 0.00463 -0.0093 0.4807 0.0077
-3.250 -0.1306 0.01136 0.00417 -0.0084 0.4740 0.0078
-3.000 -0.1064 0.01107 0.00382 -0.0075 0.4668 0.0079
-2.750 -0.0822 0.01080 0.00349 -0.0067 0.4601 0.0082
-2.500 -0.0574 0.01057 0.00321 -0.0059 0.4535 0.0087
-2.250 -0.0336 0.01032 0.00291 -0.0050 0.4466 0.0094
-2.000 -0.0083 0.01016 0.00272 -0.0044 0.4412 0.0103
-1.750 0.0166 0.00999 0.00253 -0.0036 0.4356 0.0133
-1.500 0.0400 0.00975 0.00236 -0.0027 0.4298 0.0362
-1.250 0.0648 0.00957 0.00228 -0.0020 0.4253 0.0621
-1.000 0.0891 0.00938 0.00220 -0.0013 0.4204 0.1003
-0.750 0.1065 0.00879 0.00209 0.0005 0.4155 0.2549
-0.500 0.0971 0.00707 0.00180 0.0075 0.4120 0.6677
-0.250 0.1056 0.00669 0.00214 0.0123 0.4090 0.8722
0.000 0.1299 0.00708 0.00253 0.0137 0.4049 0.8945
0.250 0.1556 0.00752 0.00294 0.0148 0.4006 0.9063
0.500 0.1829 0.00785 0.00322 0.0154 0.3957 0.9121
0.750 0.2132 0.00831 0.00366 0.0156 0.3927 0.9198
1.000 0.2401 0.00852 0.00384 0.0162 0.3891 0.9252
1.250 0.2823 0.00895 0.00421 0.0137 0.3846 0.9281
1.750 0.3448 0.00918 0.00434 0.0123 0.3775 0.9307
2.000 0.3708 0.00918 0.00432 0.0127 0.3746 0.9321
2.250 0.3933 0.00917 0.00429 0.0137 0.3713 0.9342
2.500 0.4080 0.00913 0.00421 0.0164 0.3685 0.9374
2.750 0.4280 0.00911 0.00415 0.0178 0.3651 0.9391
3.000 0.4550 0.00911 0.00413 0.0179 0.3622 0.9398
3.250 0.4829 0.00910 0.00412 0.0179 0.3598 0.9405
3.500 0.5101 0.00911 0.00411 0.0179 0.3571 0.9411
3.750 0.5365 0.00913 0.00411 0.0181 0.3542 0.9418
4.000 0.5629 0.00919 0.00415 0.0182 0.3511 0.9426
4.250 0.5878 0.00929 0.00421 0.0187 0.3473 0.9435
4.500 0.6139 0.00928 0.00421 0.0189 0.3455 0.9443
4.750 0.6396 0.00928 0.00422 0.0192 0.3431 0.9451
5.000 0.6649 0.00929 0.00424 0.0195 0.3404 0.9460
5.250 0.6897 0.00933 0.00427 0.0199 0.3377 0.9471
5.500 0.7136 0.00940 0.00432 0.0205 0.3345 0.9483
5.750 0.7372 0.00948 0.00438 0.0212 0.3312 0.9493
6.000 0.7627 0.00948 0.00441 0.0214 0.3292 0.9502
6.250 0.7884 0.00950 0.00445 0.0216 0.3266 0.9510
6.500 0.8140 0.00954 0.00450 0.0218 0.3236 0.9517
6.750 0.8393 0.00961 0.00457 0.0220 0.3205 0.9523
7.000 0.8634 0.00972 0.00466 0.0224 0.3166 0.9531
7.250 0.8897 0.00974 0.00472 0.0225 0.3141 0.9538
7.500 0.9158 0.00978 0.00480 0.0226 0.3113 0.9546
7.750 0.9414 0.00984 0.00488 0.0228 0.3077 0.9553
8.000 0.9661 0.00995 0.00499 0.0231 0.3042 0.9560
8.250 0.9903 0.01008 0.00512 0.0234 0.3002 0.9569
8.500 1.0165 0.01012 0.00522 0.0235 0.2969 0.9576
8.750 1.0416 0.01020 0.00532 0.0237 0.2930 0.9585
9.000 1.0653 0.01034 0.00546 0.0241 0.2884 0.9595
9.250 1.0894 0.01046 0.00561 0.0244 0.2842 0.9606
9.500 1.1145 0.01054 0.00573 0.0246 0.2796 0.9615
9.750 1.1378 0.01069 0.00589 0.0250 0.2744 0.9626
10.000 1.1613 0.01084 0.00606 0.0254 0.2690 0.9636
10.250 1.1850 0.01098 0.00623 0.0257 0.2629 0.9645
10.500 1.2056 0.01119 0.00643 0.0266 0.2565 0.9660
10.750 1.2279 0.01134 0.00663 0.0272 0.2504 0.9674
11.000 1.2464 0.01162 0.00689 0.0284 0.2426 0.9692
11.250 1.2664 0.01180 0.00712 0.0294 0.2354 0.9709
11.500 1.2821 0.01211 0.00742 0.0311 0.2264 0.9732
11.750 1.2977 0.01245 0.00776 0.0327 0.2171 0.9756
12.000 1.3159 0.01288 0.00819 0.0337 0.2066 0.9777
12.250 1.3326 0.01343 0.00872 0.0347 0.1946 0.9801
12.500 1.3489 0.01403 0.00931 0.0356 0.1834 0.9829
12.750 1.3641 0.01477 0.01001 0.0364 0.1710 0.9858
13.000 1.3809 0.01573 0.01093 0.0364 0.1558 0.9882
13.250 1.3965 0.01677 0.01196 0.0363 0.1435 0.9912
13.500 1.4092 0.01804 0.01320 0.0361 0.1314 0.9945
13.750 1.4232 0.01965 0.01479 0.0350 0.1189 0.9965
14.000 1.4354 0.02151 0.01665 0.0336 0.1088 0.9992
14.250 1.4268 0.02307 0.01825 0.0364 0.1035 1.0000
14.500 1.4176 0.02524 0.02043 0.0383 0.0978 1.0000
14.750 1.4144 0.02746 0.02269 0.0392 0.0926 1.0000
15.000 1.4056 0.03036 0.02561 0.0397 0.0867 1.0000
15.250 1.3981 0.03331 0.02860 0.0400 0.0815 1.0000
15.500 1.3869 0.03670 0.03203 0.0402 0.0774 1.0000
15.750 1.3807 0.03968 0.03508 0.0402 0.0742 1.0000
16.000 1.3677 0.04341 0.03886 0.0400 0.0703 1.0000
16.250 1.3552 0.04719 0.04269 0.0397 0.0672 1.0000
16.500 1.3447 0.05091 0.04647 0.0392 0.0636 1.0000
16.750 1.3327 0.05490 0.05052 0.0385 0.0612 1.0000
17.000 1.3204 0.05906 0.05473 0.0377 0.0580 1.0000
17.250 1.3119 0.06284 0.05858 0.0368 0.0555 1.0000
17.500 1.3001 0.06712 0.06290 0.0357 0.0527 1.0000
17.750 1.2903 0.07125 0.06707 0.0346 0.0496 1.0000
18.000 1.2825 0.07521 0.07110 0.0334 0.0475 1.0000
18.250 1.2693 0.07995 0.07585 0.0319 0.0443 1.0000
18.500 1.2632 0.08383 0.07979 0.0306 0.0415 1.0000
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