FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il) Reynolds number: 500,000 Max Cl/Cd: 104.8 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx6617a2-il-500000.txt Download as CSV file: xf-fx6617a2-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-17AII-182 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3100 0.08150 0.07858 -0.0995 0.8228 0.0156
-13.250 -0.3412 0.07161 0.06844 -0.1055 0.7917 0.0152
-13.000 -0.3672 0.06452 0.06112 -0.1097 0.7654 0.0147
-12.750 -0.4037 0.05705 0.05337 -0.1137 0.7477 0.0147
-12.500 -0.4295 0.05190 0.04798 -0.1157 0.7312 0.0144
-12.250 -0.4522 0.04759 0.04342 -0.1166 0.7168 0.0145
-12.000 -0.4763 0.04334 0.03890 -0.1167 0.7047 0.0142
-11.750 -0.4907 0.04041 0.03573 -0.1162 0.6935 0.0145
-11.500 -0.5064 0.03726 0.03233 -0.1152 0.6846 0.0143
-11.250 -0.5179 0.03464 0.02945 -0.1136 0.6764 0.0143
-11.000 -0.5249 0.03252 0.02710 -0.1116 0.6691 0.0145
-10.750 -0.5294 0.03066 0.02501 -0.1090 0.6624 0.0146
-10.500 -0.5294 0.02927 0.02341 -0.1062 0.6566 0.0148
-10.250 -0.5238 0.02782 0.02173 -0.1040 0.6509 0.0151
-10.000 -0.5134 0.02636 0.02002 -0.1023 0.6457 0.0153
-9.750 -0.5008 0.02547 0.01891 -0.1007 0.6409 0.0158
-9.500 -0.4860 0.02386 0.01710 -0.0995 0.6360 0.0163
-9.250 -0.4675 0.02268 0.01587 -0.0988 0.6316 0.0170
-9.000 -0.4489 0.02208 0.01520 -0.0979 0.6275 0.0178
-8.750 -0.4290 0.02132 0.01437 -0.0971 0.6238 0.0186
-8.500 -0.4088 0.02056 0.01350 -0.0962 0.6200 0.0195
-8.250 -0.3877 0.02010 0.01288 -0.0954 0.6165 0.0202
-8.000 -0.3716 0.01855 0.01130 -0.0940 0.6134 0.0216
-7.750 -0.3510 0.01801 0.01073 -0.0933 0.6104 0.0230
-7.500 -0.3292 0.01754 0.01021 -0.0925 0.6073 0.0246
-7.250 -0.3097 0.01682 0.00941 -0.0915 0.6043 0.0258
-7.000 -0.2908 0.01613 0.00869 -0.0904 0.6013 0.0272
-6.750 -0.2679 0.01581 0.00833 -0.0899 0.5984 0.0290
-6.500 -0.2442 0.01553 0.00797 -0.0895 0.5956 0.0305
-6.250 -0.2211 0.01513 0.00752 -0.0889 0.5932 0.0316
-6.000 -0.2006 0.01450 0.00688 -0.0880 0.5907 0.0334
-5.750 -0.1767 0.01417 0.00652 -0.0876 0.5882 0.0353
-5.500 -0.1521 0.01389 0.00618 -0.0872 0.5857 0.0370
-5.250 -0.1273 0.01362 0.00583 -0.0869 0.5835 0.0383
-5.000 -0.1031 0.01331 0.00544 -0.0865 0.5810 0.0409
-4.750 -0.0783 0.01301 0.00513 -0.0861 0.5788 0.0445
-4.500 -0.0533 0.01270 0.00482 -0.0857 0.5765 0.0521
-4.250 -0.0325 0.01197 0.00442 -0.0849 0.5742 0.1222
-4.000 -0.0137 0.01107 0.00401 -0.0840 0.5721 0.2548
-3.750 0.0052 0.01021 0.00364 -0.0830 0.5702 0.3836
-3.500 0.0278 0.00986 0.00360 -0.0823 0.5681 0.4814
-3.250 0.0552 0.00994 0.00367 -0.0822 0.5658 0.5189
-3.000 0.0830 0.01004 0.00376 -0.0822 0.5637 0.5389
-2.750 0.1106 0.01015 0.00386 -0.0821 0.5618 0.5567
-2.500 0.1385 0.01026 0.00395 -0.0821 0.5598 0.5689
-2.250 0.1665 0.01040 0.00403 -0.0821 0.5577 0.5793
-2.000 0.1945 0.01050 0.00412 -0.0821 0.5556 0.5872
-1.750 0.2226 0.01064 0.00419 -0.0821 0.5536 0.5952
-1.500 0.2508 0.01074 0.00425 -0.0822 0.5516 0.6013
-1.250 0.2794 0.01095 0.00441 -0.0824 0.5495 0.6077
-1.000 0.3072 0.01107 0.00448 -0.0824 0.5479 0.6138
-0.750 0.3351 0.01108 0.00453 -0.0825 0.5462 0.6176
-0.500 0.3632 0.01111 0.00456 -0.0827 0.5443 0.6203
-0.250 0.3913 0.01115 0.00458 -0.0828 0.5423 0.6234
0.000 0.4194 0.01121 0.00459 -0.0830 0.5403 0.6267
0.250 0.4476 0.01126 0.00458 -0.0832 0.5384 0.6299
0.500 0.4759 0.01128 0.00460 -0.0834 0.5366 0.6326
0.750 0.5044 0.01138 0.00468 -0.0837 0.5349 0.6355
1.000 0.5328 0.01152 0.00480 -0.0840 0.5331 0.6382
1.250 0.5603 0.01155 0.00484 -0.0841 0.5315 0.6407
1.500 0.5879 0.01160 0.00490 -0.0842 0.5297 0.6431
1.750 0.6156 0.01165 0.00494 -0.0843 0.5278 0.6454
2.000 0.6433 0.01165 0.00497 -0.0845 0.5257 0.6477
2.250 0.6712 0.01168 0.00502 -0.0847 0.5238 0.6499
2.500 0.6993 0.01174 0.00507 -0.0849 0.5221 0.6523
2.750 0.7276 0.01183 0.00514 -0.0852 0.5203 0.6549
3.000 0.7563 0.01203 0.00531 -0.0856 0.5183 0.6578
3.250 0.7829 0.01208 0.00540 -0.0856 0.5165 0.6603
3.500 0.8095 0.01210 0.00548 -0.0855 0.5145 0.6625
3.750 0.8364 0.01214 0.00558 -0.0856 0.5124 0.6648
4.000 0.8636 0.01220 0.00568 -0.0856 0.5104 0.6673
4.250 0.8910 0.01227 0.00578 -0.0858 0.5085 0.6701
4.500 0.9188 0.01236 0.00588 -0.0860 0.5068 0.6729
4.750 0.9469 0.01247 0.00598 -0.0863 0.5051 0.6756
5.000 0.9752 0.01265 0.00618 -0.0867 0.5033 0.6786
5.250 1.0010 0.01275 0.00637 -0.0865 0.5015 0.6814
5.500 1.0264 0.01282 0.00654 -0.0863 0.4994 0.6848
5.750 1.0520 0.01287 0.00666 -0.0861 0.4968 0.6882
6.000 1.0781 0.01286 0.00667 -0.0860 0.4935 0.6914
6.250 1.1050 0.01281 0.00663 -0.0860 0.4903 0.6943
6.500 1.1317 0.01290 0.00676 -0.0860 0.4870 0.6974
6.750 1.1545 0.01290 0.00688 -0.0853 0.4837 0.7008
7.000 1.1789 0.01291 0.00697 -0.0848 0.4803 0.7045
7.250 1.2043 0.01292 0.00702 -0.0846 0.4770 0.7082
7.500 1.2302 0.01294 0.00707 -0.0844 0.4735 0.7121
7.750 1.2518 0.01297 0.00722 -0.0835 0.4694 0.7167
8.000 1.2736 0.01295 0.00729 -0.0825 0.4645 0.7217
8.250 1.2965 0.01293 0.00733 -0.0818 0.4599 0.7266
8.500 1.3156 0.01292 0.00743 -0.0803 0.4532 0.7321
8.750 1.3324 0.01288 0.00738 -0.0784 0.4432 0.7385
9.000 1.3460 0.01287 0.00748 -0.0759 0.4304 0.7455
9.250 1.3593 0.01297 0.00766 -0.0734 0.4185 0.7543
9.500 1.3715 0.01313 0.00791 -0.0707 0.4084 0.7653
9.750 1.3819 0.01337 0.00823 -0.0678 0.3975 0.7813
10.000 1.3875 0.01370 0.00866 -0.0641 0.3811 0.8105
10.250 1.4204 0.01481 0.00989 -0.0678 0.3348 1.0000
10.500 1.4065 0.01653 0.01140 -0.0626 0.2980 1.0000
10.750 1.3867 0.01910 0.01378 -0.0581 0.2593 1.0000
11.000 1.3661 0.02248 0.01703 -0.0550 0.2267 1.0000
11.250 1.3439 0.02660 0.02102 -0.0529 0.1960 1.0000
11.500 1.3264 0.03058 0.02491 -0.0514 0.1704 1.0000
11.750 1.3072 0.03478 0.02902 -0.0500 0.1461 1.0000
12.000 1.2885 0.03896 0.03310 -0.0487 0.1233 1.0000
12.250 1.2696 0.04319 0.03723 -0.0475 0.1007 1.0000
12.500 1.2561 0.04706 0.04101 -0.0466 0.0805 1.0000
12.750 1.2412 0.05116 0.04500 -0.0457 0.0601 1.0000
13.000 1.2342 0.05458 0.04837 -0.0452 0.0468 1.0000
13.250 1.2262 0.05814 0.05186 -0.0447 0.0348 1.0000
13.500 1.2241 0.06115 0.05486 -0.0444 0.0288 1.0000
13.750 1.2253 0.06388 0.05762 -0.0441 0.0244 1.0000
14.000 1.2255 0.06673 0.06048 -0.0439 0.0213 1.0000
14.250 1.2277 0.06938 0.06316 -0.0438 0.0194 1.0000
14.500 1.2288 0.07219 0.06600 -0.0437 0.0181 1.0000
14.750 1.2307 0.07492 0.06878 -0.0436 0.0168 1.0000
15.000 1.2324 0.07774 0.07167 -0.0437 0.0163 1.0000
15.250 1.2326 0.08070 0.07469 -0.0436 0.0156 1.0000
15.500 1.2315 0.08388 0.07791 -0.0437 0.0149 1.0000
15.750 1.2302 0.08711 0.08120 -0.0438 0.0145 1.0000
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