EPPLER 343 AIRFOIL (e343-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 343 AIRFOIL (e343-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.43 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e343-il-1000000.txt Download as CSV file: xf-e343-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 343 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 -0.2281 0.08617 0.08355 -0.0574 0.7200 0.0096
-9.500 -0.2294 0.08261 0.07991 -0.0588 0.6987 0.0096
-9.250 -0.2318 0.07886 0.07612 -0.0605 0.6817 0.0097
-9.000 -0.2363 0.07479 0.07202 -0.0628 0.6672 0.0097
-8.750 -0.2497 0.06970 0.06691 -0.0668 0.6558 0.0097
-8.500 -0.2649 0.06563 0.06278 -0.0680 0.6443 0.0098
-8.250 -0.2807 0.06223 0.05931 -0.0669 0.6337 0.0097
-8.000 -0.2956 0.05948 0.05649 -0.0641 0.6239 0.0098
-7.750 -0.3011 0.05640 0.05331 -0.0624 0.6137 0.0097
-7.500 -0.3040 0.05331 0.05010 -0.0605 0.6047 0.0098
-7.250 -0.3040 0.05022 0.04688 -0.0584 0.5952 0.0100
-7.000 -0.3010 0.04727 0.04378 -0.0563 0.5863 0.0101
-6.750 -0.2971 0.04403 0.04037 -0.0539 0.5777 0.0104
-6.500 -0.2909 0.04061 0.03676 -0.0512 0.5698 0.0108
-6.250 -0.2843 0.03462 0.03033 -0.0465 0.5633 0.0114
-5.750 -0.2719 0.02859 0.02385 -0.0406 0.5472 0.0118
-4.750 -0.2086 0.01698 0.01077 -0.0301 0.5178 0.0084
-4.500 -0.1846 0.01489 0.00836 -0.0289 0.5103 0.0079
-4.250 -0.1594 0.01366 0.00691 -0.0281 0.5022 0.0077
-4.000 -0.1342 0.01290 0.00603 -0.0274 0.4949 0.0076
-3.750 -0.1098 0.01234 0.00535 -0.0265 0.4868 0.0079
-3.500 -0.0850 0.01192 0.00486 -0.0257 0.4801 0.0082
-3.250 -0.0605 0.01157 0.00444 -0.0249 0.4733 0.0084
-3.000 -0.0372 0.01116 0.00395 -0.0239 0.4668 0.0091
-2.750 -0.0127 0.01085 0.00362 -0.0231 0.4612 0.0097
-2.500 0.0124 0.01069 0.00342 -0.0225 0.4550 0.0105
-2.250 0.0375 0.01052 0.00320 -0.0218 0.4491 0.0111
-2.000 0.0624 0.01028 0.00293 -0.0211 0.4439 0.0117
-1.750 0.0873 0.01012 0.00274 -0.0205 0.4382 0.0130
-1.500 0.1123 0.00998 0.00257 -0.0198 0.4328 0.0153
-1.250 0.1380 0.00982 0.00243 -0.0193 0.4287 0.0208
-1.000 0.1621 0.00958 0.00229 -0.0184 0.4241 0.0482
-0.750 0.1859 0.00939 0.00222 -0.0177 0.4195 0.0946
-0.500 0.2051 0.00885 0.00214 -0.0161 0.4155 0.2454
-0.250 0.1905 0.00668 0.00195 -0.0079 0.4135 0.8035
0.000 0.2131 0.00695 0.00233 -0.0062 0.4096 0.8753
0.250 0.2372 0.00724 0.00255 -0.0050 0.4055 0.8929
0.500 0.2598 0.00743 0.00272 -0.0034 0.4009 0.9064
0.750 0.2831 0.00751 0.00280 -0.0020 0.3982 0.9167
1.000 0.3074 0.00758 0.00285 -0.0010 0.3953 0.9238
1.250 0.3321 0.00782 0.00308 0.0003 0.3919 0.9302
1.500 0.3588 0.00816 0.00339 0.0011 0.3884 0.9350
1.750 0.3862 0.00841 0.00357 0.0014 0.3840 0.9381
2.000 0.4104 0.00837 0.00351 0.0020 0.3817 0.9401
2.250 0.4377 0.00839 0.00350 0.0021 0.3793 0.9409
2.500 0.4654 0.00843 0.00352 0.0020 0.3764 0.9414
2.750 0.4926 0.00847 0.00353 0.0021 0.3732 0.9420
3.000 0.5193 0.00856 0.00357 0.0022 0.3699 0.9428
3.250 0.5454 0.00865 0.00363 0.0025 0.3666 0.9436
3.500 0.5725 0.00866 0.00364 0.0025 0.3647 0.9444
3.750 0.5993 0.00868 0.00365 0.0026 0.3622 0.9452
4.000 0.6255 0.00871 0.00367 0.0028 0.3596 0.9462
4.250 0.6510 0.00875 0.00369 0.0030 0.3570 0.9475
4.500 0.6769 0.00883 0.00374 0.0032 0.3540 0.9483
4.750 0.7027 0.00895 0.00383 0.0035 0.3504 0.9489
5.000 0.7300 0.00899 0.00389 0.0034 0.3488 0.9494
5.250 0.7571 0.00903 0.00395 0.0034 0.3466 0.9500
5.500 0.7839 0.00908 0.00401 0.0034 0.3440 0.9508
5.750 0.8101 0.00916 0.00407 0.0035 0.3414 0.9516
6.000 0.8357 0.00925 0.00416 0.0037 0.3383 0.9526
6.250 0.8600 0.00942 0.00429 0.0041 0.3345 0.9540
6.500 0.8870 0.00945 0.00436 0.0040 0.3327 0.9550
6.750 0.9136 0.00950 0.00444 0.0040 0.3303 0.9557
7.000 0.9397 0.00956 0.00452 0.0041 0.3274 0.9564
7.250 0.9651 0.00965 0.00462 0.0043 0.3242 0.9573
7.500 0.9895 0.00979 0.00475 0.0047 0.3209 0.9584
7.750 1.0146 0.00991 0.00488 0.0049 0.3177 0.9595
8.000 1.0409 0.00996 0.00498 0.0049 0.3150 0.9607
8.250 1.0668 0.01005 0.00509 0.0049 0.3117 0.9619
8.500 1.0910 0.01016 0.00521 0.0053 0.3082 0.9629
8.750 1.1132 0.01033 0.00537 0.0061 0.3038 0.9642
9.000 1.1384 0.01040 0.00550 0.0063 0.3010 0.9654
9.250 1.1631 0.01048 0.00562 0.0065 0.2971 0.9668
9.500 1.1860 0.01061 0.00576 0.0071 0.2925 0.9687
9.750 1.2069 0.01079 0.00594 0.0080 0.2879 0.9706
10.000 1.2315 0.01087 0.00608 0.0083 0.2840 0.9721
10.250 1.2538 0.01101 0.00625 0.0089 0.2787 0.9740
10.500 1.2718 0.01121 0.00645 0.0103 0.2732 0.9768
10.750 1.2965 0.01133 0.00663 0.0104 0.2677 0.9786
11.000 1.3185 0.01160 0.00689 0.0109 0.2610 0.9808
11.250 1.3424 0.01184 0.00717 0.0110 0.2550 0.9830
11.500 1.3646 0.01218 0.00751 0.0113 0.2462 0.9856
11.750 1.3916 0.01254 0.00788 0.0105 0.2371 0.9869
12.000 1.4167 0.01302 0.00835 0.0099 0.2268 0.9885
12.250 1.4402 0.01360 0.00891 0.0095 0.2151 0.9903
12.500 1.4619 0.01427 0.00954 0.0092 0.2021 0.9924
12.750 1.4822 0.01499 0.01025 0.0090 0.1893 0.9952
13.000 1.5006 0.01591 0.01113 0.0089 0.1753 0.9991
13.250 1.5017 0.01661 0.01183 0.0122 0.1667 1.0000
13.500 1.4990 0.01755 0.01277 0.0158 0.1590 1.0000
13.750 1.4964 0.01888 0.01407 0.0186 0.1486 1.0000
14.000 1.4971 0.02026 0.01547 0.0206 0.1398 1.0000
14.250 1.4959 0.02198 0.01720 0.0223 0.1323 1.0000
14.500 1.4871 0.02446 0.01965 0.0238 0.1212 1.0000
14.750 1.4883 0.02637 0.02162 0.0246 0.1162 1.0000
15.000 1.4746 0.02968 0.02491 0.0255 0.1054 1.0000
15.250 1.4716 0.03221 0.02750 0.0259 0.1018 1.0000
15.500 1.4618 0.03545 0.03078 0.0262 0.0966 1.0000
15.750 1.4545 0.03853 0.03392 0.0264 0.0923 1.0000
16.000 1.4296 0.04342 0.03880 0.0264 0.0823 1.0000
16.250 1.4330 0.04561 0.04112 0.0263 0.0852 1.0000
16.500 1.4025 0.05142 0.04689 0.0258 0.0740 1.0000
16.750 1.3935 0.05510 0.05064 0.0253 0.0712 1.0000
17.000 1.3801 0.05935 0.05493 0.0247 0.0679 1.0000
17.250 1.3737 0.06289 0.05855 0.0240 0.0670 1.0000
17.500 1.3610 0.06724 0.06295 0.0231 0.0622 1.0000
17.750 1.3471 0.07182 0.06755 0.0220 0.0585 1.0000
18.000 1.3408 0.07553 0.07132 0.0211 0.0562 1.0000
18.250 1.3291 0.08003 0.07586 0.0198 0.0520 1.0000
18.500 1.3179 0.08454 0.08039 0.0185 0.0491 1.0000
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