EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER EA 6(-1)-009 AIRFOIL (ea61009-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.86 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ea61009-il-1000000.txt Download as CSV file: xf-ea61009-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER EA 6(-1)-009 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
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0154 0.13127 0.12944 0.0304 1.0000 0.0097
-16.500 -1.1581 0.09418 0.09202 0.0082 1.0000 0.0088
-16.250 -1.2393 0.07197 0.06951 -0.0064 1.0000 0.0084
-16.000 -1.2731 0.06087 0.05821 -0.0144 1.0000 0.0085
-15.750 -1.3032 0.05210 0.04922 -0.0203 1.0000 0.0083
-15.500 -1.3158 0.04712 0.04409 -0.0229 1.0000 0.0084
-15.250 -1.3292 0.04262 0.03943 -0.0246 1.0000 0.0085
-15.000 -1.3388 0.03907 0.03573 -0.0251 1.0000 0.0085
-14.750 -1.3444 0.03625 0.03278 -0.0249 1.0000 0.0087
-14.500 -1.3496 0.03376 0.03015 -0.0240 1.0000 0.0087
-14.250 -1.3515 0.03178 0.02804 -0.0226 1.0000 0.0088
-14.000 -1.3481 0.03039 0.02653 -0.0210 1.0000 0.0090
-13.750 -1.3482 0.02894 0.02495 -0.0185 1.0000 0.0091
-13.500 -1.3403 0.02794 0.02385 -0.0165 1.0000 0.0092
-13.250 -1.3392 0.02585 0.02156 -0.0143 1.0000 0.0096
-13.000 -1.3292 0.02434 0.01993 -0.0128 1.0000 0.0100
-12.750 -1.3137 0.02324 0.01875 -0.0117 1.0000 0.0104
-12.500 -1.2961 0.02229 0.01771 -0.0108 1.0000 0.0107
-12.250 -1.2773 0.02141 0.01672 -0.0100 1.0000 0.0111
-12.000 -1.2576 0.02056 0.01578 -0.0092 1.0000 0.0115
-11.750 -1.2368 0.01980 0.01492 -0.0086 1.0000 0.0119
-11.500 -1.2168 0.01887 0.01387 -0.0078 1.0000 0.0124
-11.250 -1.1968 0.01788 0.01281 -0.0071 1.0000 0.0133
-11.000 -1.1744 0.01721 0.01210 -0.0066 1.0000 0.0141
-10.750 -1.1512 0.01660 0.01142 -0.0061 1.0000 0.0149
-10.500 -1.1280 0.01598 0.01073 -0.0056 1.0000 0.0158
-10.250 -1.1045 0.01535 0.01009 -0.0052 1.0000 0.0175
-10.000 -1.0795 0.01495 0.00966 -0.0050 1.0000 0.0191
-9.750 -1.0548 0.01448 0.00919 -0.0047 1.0000 0.0211
-9.500 -1.0283 0.01430 0.00902 -0.0045 1.0000 0.0231
-9.250 -1.0015 0.01416 0.00885 -0.0044 1.0000 0.0244
-9.000 -0.9756 0.01385 0.00857 -0.0042 1.0000 0.0265
-8.750 -0.9478 0.01391 0.00865 -0.0043 1.0000 0.0280
-8.500 -0.9199 0.01395 0.00869 -0.0043 1.0000 0.0294
-8.250 -0.8920 0.01402 0.00874 -0.0043 1.0000 0.0303
-8.000 -0.8670 0.01347 0.00814 -0.0041 1.0000 0.0317
-7.750 -0.8401 0.01330 0.00799 -0.0040 1.0000 0.0329
-7.500 -0.8126 0.01325 0.00795 -0.0040 1.0000 0.0339
-7.250 -0.7851 0.01318 0.00788 -0.0040 1.0000 0.0350
-7.000 -0.7575 0.01311 0.00779 -0.0040 1.0000 0.0362
-6.750 -0.7301 0.01296 0.00762 -0.0040 1.0000 0.0371
-6.500 -0.7021 0.01295 0.00758 -0.0041 1.0000 0.0378
-6.250 -0.6700 0.01214 0.00672 -0.0054 0.9701 0.0392
-6.000 -0.6392 0.01165 0.00620 -0.0062 0.9427 0.0408
-5.750 -0.6140 0.01144 0.00593 -0.0056 0.9249 0.0418
-5.500 -0.5885 0.01119 0.00564 -0.0052 0.9132 0.0427
-5.250 -0.5624 0.01097 0.00537 -0.0048 0.9043 0.0438
-4.750 -0.5100 0.01044 0.00476 -0.0041 0.8880 0.0457
-4.500 -0.4837 0.01023 0.00449 -0.0037 0.8806 0.0464
-4.250 -0.4566 0.01001 0.00425 -0.0035 0.8738 0.0470
-4.000 -0.4296 0.00987 0.00407 -0.0033 0.8675 0.0475
-3.750 -0.4029 0.00953 0.00370 -0.0031 0.8615 0.0483
-3.500 -0.3769 0.00903 0.00313 -0.0028 0.8547 0.0500
-3.250 -0.3501 0.00874 0.00282 -0.0025 0.8472 0.0515
-3.000 -0.3230 0.00854 0.00258 -0.0023 0.8388 0.0529
-2.750 -0.2957 0.00835 0.00237 -0.0020 0.8284 0.0543
-2.500 -0.2684 0.00821 0.00219 -0.0018 0.8200 0.0556
-2.250 -0.2405 0.00806 0.00203 -0.0017 0.8115 0.0570
-2.000 -0.2128 0.00795 0.00188 -0.0016 0.8030 0.0583
-1.750 -0.1852 0.00784 0.00175 -0.0014 0.7919 0.0591
-1.500 -0.1575 0.00770 0.00157 -0.0012 0.7774 0.0612
-1.250 -0.1298 0.00757 0.00141 -0.0010 0.7625 0.0658
-1.000 -0.1020 0.00745 0.00129 -0.0009 0.7472 0.0711
-0.750 -0.0756 0.00696 0.00112 -0.0008 0.7303 0.1793
-0.500 -0.0504 0.00623 0.00094 -0.0007 0.7064 0.3514
-0.250 -0.0258 0.00558 0.00079 -0.0004 0.6701 0.5240
0.000 0.0000 0.00540 0.00076 0.0000 0.6203 0.6202
0.250 0.0258 0.00557 0.00079 0.0004 0.5246 0.6704
0.500 0.0504 0.00623 0.00094 0.0007 0.3502 0.7061
0.750 0.0757 0.00697 0.00112 0.0008 0.1786 0.7299
1.000 0.1020 0.00745 0.00129 0.0009 0.0711 0.7471
1.250 0.1298 0.00757 0.00141 0.0010 0.0657 0.7624
1.500 0.1575 0.00770 0.00157 0.0012 0.0611 0.7774
1.750 0.1851 0.00784 0.00175 0.0014 0.0591 0.7920
2.000 0.2128 0.00794 0.00188 0.0016 0.0583 0.8030
2.250 0.2405 0.00806 0.00203 0.0017 0.0570 0.8115
2.500 0.2684 0.00821 0.00219 0.0018 0.0556 0.8200
2.750 0.2957 0.00836 0.00237 0.0020 0.0543 0.8283
3.000 0.3230 0.00854 0.00258 0.0023 0.0529 0.8387
3.250 0.3501 0.00875 0.00282 0.0025 0.0515 0.8473
3.500 0.3769 0.00903 0.00314 0.0028 0.0499 0.8547
3.750 0.4028 0.00954 0.00371 0.0031 0.0483 0.8615
4.000 0.4295 0.00988 0.00407 0.0033 0.0475 0.8675
4.250 0.4566 0.01001 0.00425 0.0036 0.0470 0.8738
4.500 0.4837 0.01023 0.00449 0.0037 0.0464 0.8807
4.750 0.5100 0.01044 0.00476 0.0041 0.0457 0.8880
5.250 0.5624 0.01097 0.00537 0.0048 0.0439 0.9043
5.500 0.5886 0.01119 0.00563 0.0052 0.0427 0.9133
5.750 0.6140 0.01144 0.00593 0.0056 0.0418 0.9250
6.000 0.6392 0.01165 0.00620 0.0062 0.0409 0.9430
6.250 0.6703 0.01212 0.00670 0.0053 0.0393 0.9702
6.500 0.7023 0.01293 0.00756 0.0040 0.0378 1.0000
6.750 0.7303 0.01295 0.00761 0.0040 0.0371 1.0000
7.000 0.7576 0.01312 0.00779 0.0040 0.0362 1.0000
7.250 0.7852 0.01320 0.00789 0.0040 0.0350 1.0000
7.500 0.8127 0.01325 0.00795 0.0040 0.0339 1.0000
7.750 0.8403 0.01329 0.00798 0.0040 0.0329 1.0000
8.000 0.8671 0.01348 0.00815 0.0040 0.0316 1.0000
8.250 0.8922 0.01401 0.00873 0.0043 0.0303 1.0000
8.500 0.9203 0.01392 0.00866 0.0042 0.0293 1.0000
8.750 0.9480 0.01390 0.00864 0.0042 0.0279 1.0000
9.000 0.9759 0.01385 0.00856 0.0042 0.0265 1.0000
9.250 1.0019 0.01415 0.00884 0.0044 0.0244 1.0000
9.500 1.0286 0.01429 0.00902 0.0045 0.0230 1.0000
9.750 1.0550 0.01448 0.00918 0.0046 0.0211 1.0000
10.000 1.0797 0.01495 0.00966 0.0049 0.0191 1.0000
10.250 1.1047 0.01536 0.01010 0.0052 0.0176 1.0000
10.500 1.1282 0.01599 0.01074 0.0056 0.0158 1.0000
10.750 1.1515 0.01661 0.01143 0.0061 0.0149 1.0000
11.000 1.1747 0.01720 0.01209 0.0065 0.0141 1.0000
11.250 1.1970 0.01788 0.01282 0.0070 0.0133 1.0000
11.500 1.2171 0.01886 0.01387 0.0078 0.0124 1.0000
11.750 1.2371 0.01980 0.01492 0.0085 0.0119 1.0000
12.000 1.2579 0.02057 0.01579 0.0092 0.0115 1.0000
12.250 1.2777 0.02142 0.01674 0.0099 0.0111 1.0000
12.500 1.2967 0.02229 0.01770 0.0107 0.0107 1.0000
12.750 1.3143 0.02325 0.01875 0.0116 0.0103 1.0000
13.000 1.3298 0.02436 0.01995 0.0126 0.0100 1.0000
13.250 1.3403 0.02583 0.02154 0.0141 0.0096 1.0000
13.500 1.3404 0.02802 0.02393 0.0164 0.0092 1.0000
13.750 1.3490 0.02898 0.02500 0.0184 0.0091 1.0000
14.000 1.3510 0.03030 0.02643 0.0207 0.0090 1.0000
14.250 1.3505 0.03196 0.02822 0.0226 0.0089 1.0000
14.500 1.3485 0.03396 0.03035 0.0239 0.0088 1.0000
14.750 1.3482 0.03605 0.03256 0.0247 0.0085 1.0000
15.000 1.3398 0.03910 0.03577 0.0249 0.0085 1.0000
15.250 1.3352 0.04210 0.03890 0.0245 0.0084 1.0000
15.500 1.3211 0.04662 0.04358 0.0229 0.0084 1.0000
15.750 1.3070 0.05177 0.04888 0.0203 0.0083 1.0000
16.000 1.2782 0.06022 0.05754 0.0147 0.0084 1.0000
16.250 1.2367 0.07281 0.07037 0.0056 0.0085 1.0000
16.500 1.1436 0.09753 0.09540 -0.0105 0.0089 1.0000
16.750 1.0199 0.13045 0.12861 -0.0300 0.0097 1.0000
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Polar data table (+)
Polar graphs
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