FX 66-S-171 AIRFOIL (fx66s171-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-S-171 AIRFOIL (fx66s171-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.56 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66s171-il-1000000.txt Download as CSV file: xf-fx66s171-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-171 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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.5942 0.09737 0.09549 -0.0483 1.0000 0.0082
-15.000 -0.6479 0.08187 0.07976 -0.0574 1.0000 0.0081
-14.750 -0.7005 0.06855 0.06616 -0.0657 1.0000 0.0078
-14.500 -0.7149 0.06263 0.06013 -0.0694 1.0000 0.0078
-14.250 -0.7324 0.05683 0.05418 -0.0729 1.0000 0.0078
-14.000 -0.7502 0.05141 0.04861 -0.0758 1.0000 0.0078
-13.750 -0.7590 0.04741 0.04450 -0.0778 1.0000 0.0078
-13.500 -0.7714 0.04318 0.04013 -0.0796 1.0000 0.0078
-13.250 -0.7653 0.04017 0.03703 -0.0825 0.9988 0.0080
-13.000 -0.7061 0.03407 0.03056 -0.1006 0.9298 0.0081
-12.750 -0.6592 0.03082 0.02669 -0.1118 0.8277 0.0083
-12.500 -0.6573 0.02934 0.02494 -0.1111 0.7832 0.0084
-12.250 -0.6581 0.02747 0.02284 -0.1103 0.7540 0.0085
-12.000 -0.6561 0.02581 0.02101 -0.1095 0.7332 0.0085
-11.750 -0.6513 0.02449 0.01953 -0.1087 0.7156 0.0086
-11.500 -0.6494 0.02312 0.01802 -0.1073 0.7015 0.0087
-11.250 -0.6472 0.02212 0.01688 -0.1050 0.6893 0.0087
-11.000 -0.6410 0.02139 0.01603 -0.1026 0.6785 0.0088
-10.750 -0.6279 0.02064 0.01517 -0.1013 0.6685 0.0088
-10.500 -0.6246 0.01898 0.01334 -0.0989 0.6604 0.0091
-10.250 -0.6116 0.01799 0.01225 -0.0975 0.6521 0.0094
-10.000 -0.5932 0.01736 0.01153 -0.0966 0.6448 0.0097
-9.750 -0.5722 0.01689 0.01101 -0.0960 0.6375 0.0101
-9.500 -0.5507 0.01644 0.01048 -0.0953 0.6311 0.0104
-9.250 -0.5291 0.01592 0.00989 -0.0947 0.6247 0.0108
-9.000 -0.5072 0.01544 0.00932 -0.0941 0.6185 0.0111
-8.750 -0.4841 0.01497 0.00878 -0.0937 0.6130 0.0114
-8.500 -0.4602 0.01459 0.00832 -0.0933 0.6072 0.0117
-8.250 -0.4402 0.01380 0.00742 -0.0924 0.6018 0.0124
-8.000 -0.4158 0.01336 0.00695 -0.0921 0.5969 0.0131
-7.750 -0.3908 0.01303 0.00656 -0.0919 0.5918 0.0138
-7.500 -0.3655 0.01275 0.00621 -0.0916 0.5867 0.0147
-7.250 -0.3405 0.01230 0.00570 -0.0914 0.5825 0.0160
-7.000 -0.3149 0.01196 0.00534 -0.0912 0.5778 0.0176
-6.750 -0.2884 0.01177 0.00508 -0.0910 0.5735 0.0193
-6.500 -0.2628 0.01140 0.00468 -0.0909 0.5698 0.0221
-6.250 -0.2356 0.01119 0.00445 -0.0909 0.5662 0.0244
-6.000 -0.2091 0.01089 0.00413 -0.0908 0.5626 0.0280
-5.750 -0.1820 0.01072 0.00392 -0.0907 0.5591 0.0310
-5.500 -0.1555 0.01047 0.00366 -0.0907 0.5557 0.0371
-5.250 -0.1281 0.01021 0.00342 -0.0907 0.5529 0.0461
-5.000 -0.1010 0.00993 0.00319 -0.0907 0.5497 0.0624
-4.750 -0.0746 0.00958 0.00295 -0.0907 0.5463 0.0941
-4.500 -0.0486 0.00917 0.00271 -0.0907 0.5430 0.1447
-4.250 -0.0231 0.00865 0.00244 -0.0907 0.5403 0.2180
-4.000 0.0028 0.00810 0.00222 -0.0908 0.5380 0.3105
-3.750 0.0304 0.00787 0.00211 -0.0909 0.5354 0.3540
-3.500 0.0584 0.00774 0.00203 -0.0910 0.5327 0.3842
-3.250 0.0866 0.00767 0.00200 -0.0911 0.5301 0.4083
-3.000 0.1150 0.00768 0.00199 -0.0913 0.5274 0.4285
-2.750 0.1437 0.00769 0.00199 -0.0914 0.5253 0.4447
-2.500 0.1726 0.00768 0.00200 -0.0916 0.5234 0.4558
-2.250 0.2016 0.00769 0.00199 -0.0919 0.5215 0.4641
-2.000 0.2306 0.00774 0.00201 -0.0921 0.5194 0.4755
-1.750 0.2593 0.00775 0.00203 -0.0922 0.5172 0.4835
-1.500 0.2880 0.00782 0.00203 -0.0924 0.5148 0.4893
-1.250 0.3163 0.00787 0.00206 -0.0926 0.5120 0.4957
-1.000 0.3451 0.00791 0.00209 -0.0928 0.5101 0.5012
-0.750 0.3742 0.00794 0.00209 -0.0930 0.5084 0.5054
-0.500 0.4030 0.00793 0.00208 -0.0933 0.5065 0.5089
-0.250 0.4317 0.00793 0.00209 -0.0935 0.5045 0.5123
0.000 0.4604 0.00795 0.00210 -0.0937 0.5025 0.5156
0.250 0.4890 0.00800 0.00212 -0.0939 0.5006 0.5188
0.500 0.5175 0.00807 0.00216 -0.0941 0.4985 0.5216
0.750 0.5457 0.00814 0.00222 -0.0942 0.4958 0.5251
1.000 0.5744 0.00813 0.00224 -0.0945 0.4945 0.5285
1.250 0.6032 0.00815 0.00227 -0.0947 0.4928 0.5319
1.500 0.6319 0.00818 0.00231 -0.0949 0.4910 0.5352
1.750 0.6605 0.00821 0.00235 -0.0952 0.4893 0.5385
2.000 0.6889 0.00823 0.00239 -0.0954 0.4875 0.5425
2.250 0.7172 0.00827 0.00245 -0.0956 0.4857 0.5464
2.500 0.7454 0.00835 0.00251 -0.0957 0.4837 0.5503
2.750 0.7735 0.00846 0.00261 -0.0959 0.4814 0.5541
3.000 0.8018 0.00849 0.00269 -0.0961 0.4799 0.5583
3.250 0.8301 0.00851 0.00275 -0.0963 0.4783 0.5628
3.500 0.8585 0.00855 0.00281 -0.0965 0.4764 0.5674
3.750 0.8866 0.00857 0.00288 -0.0967 0.4743 0.5728
4.000 0.9146 0.00860 0.00295 -0.0969 0.4722 0.5785
4.250 0.9425 0.00866 0.00303 -0.0970 0.4700 0.5842
4.500 0.9699 0.00875 0.00314 -0.0971 0.4672 0.5912
5.000 1.0255 0.00882 0.00335 -0.0974 0.4627 0.6091
5.250 1.0532 0.00885 0.00345 -0.0975 0.4604 0.6197
5.500 1.0808 0.00890 0.00356 -0.0976 0.4581 0.6312
5.750 1.1080 0.00895 0.00367 -0.0977 0.4557 0.6442
6.000 1.1347 0.00904 0.00381 -0.0976 0.4529 0.6593
6.250 1.1616 0.00911 0.00396 -0.0977 0.4502 0.6779
6.500 1.1887 0.00911 0.00409 -0.0977 0.4477 0.7008
6.750 1.2153 0.00911 0.00424 -0.0976 0.4450 0.7309
7.000 1.2410 0.00910 0.00439 -0.0974 0.4420 0.7766
7.250 1.2630 0.00904 0.00455 -0.0963 0.4379 0.8596
7.500 1.2947 0.00887 0.00463 -0.0973 0.4306 1.0000
7.750 1.3197 0.00897 0.00471 -0.0969 0.4197 1.0000
8.000 1.3443 0.00911 0.00481 -0.0966 0.4049 1.0000
8.250 1.3676 0.00934 0.00500 -0.0960 0.3890 1.0000
8.500 1.3896 0.00964 0.00525 -0.0952 0.3737 1.0000
8.750 1.4101 0.01001 0.00557 -0.0942 0.3552 1.0000
9.000 1.4273 0.01053 0.00598 -0.0927 0.3323 1.0000
9.250 1.4419 0.01114 0.00647 -0.0907 0.3093 1.0000
9.500 1.4533 0.01184 0.00705 -0.0882 0.2803 1.0000
9.750 1.4509 0.01288 0.00786 -0.0834 0.2415 1.0000
10.000 1.4383 0.01418 0.00894 -0.0770 0.2022 1.0000
10.250 1.4209 0.01580 0.01036 -0.0706 0.1657 1.0000
10.500 1.4079 0.01751 0.01195 -0.0657 0.1397 1.0000
10.750 1.3919 0.01977 0.01410 -0.0614 0.1136 1.0000
11.000 1.3788 0.02232 0.01658 -0.0583 0.0916 1.0000
11.250 1.3665 0.02520 0.01939 -0.0560 0.0729 1.0000
11.500 1.3556 0.02822 0.02236 -0.0542 0.0566 1.0000
11.750 1.3449 0.03138 0.02548 -0.0526 0.0434 1.0000
12.000 1.3376 0.03434 0.02843 -0.0514 0.0336 1.0000
12.250 1.3316 0.03723 0.03132 -0.0504 0.0262 1.0000
12.500 1.3261 0.04015 0.03424 -0.0494 0.0205 1.0000
12.750 1.3232 0.04290 0.03701 -0.0487 0.0175 1.0000
13.000 1.3237 0.04542 0.03957 -0.0482 0.0156 1.0000
13.250 1.3232 0.04810 0.04230 -0.0478 0.0140 1.0000
13.500 1.3216 0.05097 0.04521 -0.0474 0.0125 1.0000
13.750 1.3254 0.05332 0.04763 -0.0472 0.0118 1.0000
14.000 1.3257 0.05612 0.05047 -0.0471 0.0107 1.0000
14.250 1.3255 0.05900 0.05340 -0.0470 0.0101 1.0000
14.500 1.3266 0.06180 0.05626 -0.0469 0.0093 1.0000
14.750 1.3290 0.06451 0.05903 -0.0470 0.0089 1.0000
15.000 1.3321 0.06715 0.06172 -0.0471 0.0084 1.0000
15.250 1.3325 0.07017 0.06480 -0.0473 0.0080 1.0000
15.500 1.3299 0.07360 0.06828 -0.0476 0.0074 1.0000
15.750 1.3264 0.07726 0.07201 -0.0480 0.0071 1.0000
16.000 1.3315 0.07984 0.07465 -0.0484 0.0069 1.0000
16.250 1.3329 0.08293 0.07781 -0.0488 0.0067 1.0000
16.500 1.3362 0.08579 0.08073 -0.0493 0.0063 1.0000
16.750 1.3374 0.08901 0.08401 -0.0500 0.0061 1.0000
17.000 1.3397 0.09207 0.08712 -0.0506 0.0058 1.0000
17.250 1.3387 0.09569 0.09079 -0.0515 0.0056 1.0000
17.500 1.3333 0.09994 0.09512 -0.0525 0.0053 1.0000
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Polar data table (+)
Polar graphs
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