FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-163 AIRFOIL (fx61163-il) Reynolds number: 200,000 Max Cl/Cd: 72.65 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61163-il-200000-n5.txt Download as CSV file: xf-fx61163-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-163 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5533 0.06026 0.05608 -0.0681 1.0001 0.0102
-10.750 -0.5702 0.05639 0.05209 -0.0684 1.0001 0.0102
-10.500 -0.5861 0.05307 0.04865 -0.0678 1.0001 0.0102
-10.250 -0.6025 0.05020 0.04565 -0.0662 1.0001 0.0102
-10.000 -0.6128 0.04693 0.04217 -0.0659 0.9920 0.0102
-9.750 -0.6101 0.04292 0.03781 -0.0683 0.9597 0.0102
-9.500 -0.5898 0.03842 0.03286 -0.0731 0.9292 0.0103
-9.250 -0.5566 0.03462 0.02865 -0.0785 0.9029 0.0105
-9.000 -0.5194 0.03210 0.02579 -0.0832 0.8726 0.0109
-8.750 -0.4875 0.03053 0.02394 -0.0860 0.8418 0.0116
-8.500 -0.4622 0.02896 0.02202 -0.0869 0.8157 0.0123
-8.250 -0.4390 0.02738 0.02009 -0.0869 0.7953 0.0128
-8.000 -0.4162 0.02590 0.01829 -0.0863 0.7785 0.0130
-7.750 -0.3933 0.02463 0.01678 -0.0857 0.7647 0.0132
-7.500 -0.3705 0.02355 0.01550 -0.0849 0.7525 0.0134
-7.250 -0.3480 0.02260 0.01440 -0.0842 0.7415 0.0137
-7.000 -0.3258 0.02174 0.01342 -0.0835 0.7319 0.0139
-6.750 -0.3056 0.02072 0.01233 -0.0829 0.7230 0.0144
-6.500 -0.2838 0.01991 0.01145 -0.0827 0.7149 0.0150
-6.250 -0.2611 0.01919 0.01064 -0.0826 0.7079 0.0158
-6.000 -0.2375 0.01850 0.00986 -0.0827 0.7015 0.0167
-5.750 -0.2128 0.01792 0.00915 -0.0830 0.6952 0.0182
-5.500 -0.1880 0.01727 0.00842 -0.0834 0.6897 0.0207
-5.250 -0.1618 0.01674 0.00780 -0.0838 0.6838 0.0238
-5.000 -0.1351 0.01617 0.00715 -0.0843 0.6788 0.0296
-4.750 -0.1078 0.01553 0.00654 -0.0851 0.6745 0.0516
-4.500 -0.0801 0.01406 0.00574 -0.0875 0.6697 0.1936
-4.250 -0.0488 0.01225 0.00544 -0.0909 0.6651 0.5217
-4.000 -0.0215 0.01270 0.00598 -0.0902 0.6612 0.5853
-3.750 0.0068 0.01313 0.00635 -0.0899 0.6568 0.6103
-3.500 0.0344 0.01349 0.00663 -0.0894 0.6525 0.6230
-3.250 0.0636 0.01361 0.00659 -0.0897 0.6487 0.6299
-3.000 0.0920 0.01371 0.00657 -0.0897 0.6451 0.6337
-2.750 0.1220 0.01373 0.00648 -0.0904 0.6408 0.6396
-2.500 0.1512 0.01378 0.00642 -0.0907 0.6368 0.6440
-2.250 0.1793 0.01388 0.00644 -0.0907 0.6332 0.6472
-2.000 0.2085 0.01395 0.00640 -0.0911 0.6300 0.6511
-1.750 0.2399 0.01391 0.00625 -0.0922 0.6259 0.6570
-1.500 0.2675 0.01399 0.00631 -0.0921 0.6222 0.6593
-1.250 0.2957 0.01407 0.00633 -0.0922 0.6188 0.6620
-0.750 0.3549 0.01413 0.00626 -0.0933 0.6114 0.6691
-0.500 0.3849 0.01413 0.00620 -0.0941 0.6071 0.6726
-0.250 0.4129 0.01420 0.00624 -0.0941 0.6033 0.6747
0.000 0.4414 0.01428 0.00626 -0.0943 0.6000 0.6770
0.250 0.4700 0.01432 0.00632 -0.0947 0.5959 0.6799
0.500 0.4997 0.01435 0.00633 -0.0953 0.5920 0.6834
0.750 0.5305 0.01438 0.00629 -0.0962 0.5885 0.6869
1.000 0.5585 0.01447 0.00636 -0.0963 0.5853 0.6888
1.250 0.5861 0.01453 0.00648 -0.0964 0.5810 0.6910
1.500 0.6144 0.01458 0.00656 -0.0967 0.5767 0.6934
1.750 0.6434 0.01464 0.00660 -0.0971 0.5726 0.6962
2.000 0.6732 0.01469 0.00663 -0.0978 0.5684 0.6994
2.250 0.7022 0.01473 0.00671 -0.0983 0.5633 0.7021
2.500 0.7299 0.01479 0.00681 -0.0984 0.5591 0.7038
2.750 0.7580 0.01488 0.00690 -0.0985 0.5556 0.7058
3.000 0.7856 0.01496 0.00707 -0.0987 0.5506 0.7082
3.250 0.8139 0.01503 0.00718 -0.0990 0.5456 0.7108
3.500 0.8432 0.01510 0.00725 -0.0995 0.5415 0.7135
3.750 0.8725 0.01518 0.00739 -0.1002 0.5362 0.7163
4.000 0.8992 0.01524 0.00753 -0.1001 0.5302 0.7180
4.250 0.9263 0.01531 0.00765 -0.1001 0.5248 0.7199
4.500 0.9532 0.01540 0.00785 -0.1001 0.5180 0.7221
4.750 0.9808 0.01549 0.00798 -0.1002 0.5126 0.7244
5.000 1.0083 0.01559 0.00818 -0.1004 0.5052 0.7271
5.250 1.0362 0.01566 0.00827 -0.1007 0.4974 0.7298
5.500 1.0629 0.01576 0.00847 -0.1007 0.4885 0.7319
5.750 1.0886 0.01586 0.00863 -0.1004 0.4804 0.7338
6.000 1.1139 0.01597 0.00884 -0.1002 0.4698 0.7359
6.250 1.1394 0.01612 0.00906 -0.0999 0.4591 0.7381
6.500 1.1649 0.01628 0.00928 -0.0998 0.4483 0.7404
6.750 1.1895 0.01648 0.00950 -0.0994 0.4335 0.7430
7.000 1.2137 0.01673 0.00976 -0.0991 0.4169 0.7457
7.250 1.2358 0.01701 0.01008 -0.0983 0.4016 0.7475
7.500 1.2578 0.01734 0.01045 -0.0976 0.3872 0.7493
7.750 1.2791 0.01771 0.01087 -0.0967 0.3721 0.7513
8.000 1.2997 0.01814 0.01134 -0.0958 0.3564 0.7537
8.250 1.3181 0.01867 0.01186 -0.0946 0.3373 0.7564
8.500 1.3352 0.01928 0.01245 -0.0933 0.3138 0.7590
8.750 1.3479 0.02007 0.01316 -0.0913 0.2870 0.7612
9.000 1.3567 0.02096 0.01398 -0.0888 0.2584 0.7631
9.250 1.3602 0.02197 0.01491 -0.0855 0.2320 0.7653
9.500 1.3638 0.02322 0.01607 -0.0826 0.2056 0.7679
9.750 1.3668 0.02462 0.01740 -0.0799 0.1820 0.7708
10.000 1.3678 0.02626 0.01900 -0.0775 0.1608 0.7737
10.250 1.3679 0.02812 0.02081 -0.0754 0.1399 0.7762
10.500 1.3665 0.03025 0.02291 -0.0736 0.1220 0.7783
10.750 1.3661 0.03251 0.02514 -0.0722 0.1042 0.7807
11.000 1.3653 0.03498 0.02759 -0.0712 0.0892 0.7833
11.250 1.3656 0.03745 0.03008 -0.0704 0.0764 0.7861
11.500 1.3662 0.04001 0.03265 -0.0698 0.0666 0.7892
11.750 1.3654 0.04267 0.03534 -0.0691 0.0589 0.7918
12.000 1.3658 0.04525 0.03800 -0.0685 0.0523 0.7944
12.250 1.3658 0.04792 0.04075 -0.0680 0.0463 0.7973
12.500 1.3653 0.05068 0.04357 -0.0676 0.0396 0.8002
12.750 1.3648 0.05349 0.04647 -0.0673 0.0349 0.8032
13.000 1.3621 0.05654 0.04957 -0.0669 0.0306 0.8060
13.250 1.3605 0.05950 0.05263 -0.0666 0.0271 0.8088
13.500 1.3572 0.06274 0.05593 -0.0665 0.0239 0.8120
13.750 1.3552 0.06596 0.05925 -0.0665 0.0214 0.8156
14.250 1.3487 0.07282 0.06632 -0.0667 0.0169 0.8233
14.500 1.3468 0.07619 0.06982 -0.0669 0.0147 0.8277
14.750 1.3434 0.07987 0.07360 -0.0673 0.0130 0.8324
15.000 1.3383 0.08378 0.07763 -0.0678 0.0115 0.8371
15.250 1.3349 0.08750 0.08150 -0.0683 0.0101 0.8425
15.500 1.3302 0.09153 0.08564 -0.0690 0.0091 0.8486
15.750 1.3237 0.09579 0.09001 -0.0698 0.0084 0.8551
16.250 1.3126 0.10416 0.09873 -0.0715 0.0074 0.8736
16.500 1.3059 0.10840 0.10313 -0.0723 0.0071 0.8885
16.750 1.2967 0.11235 0.10725 -0.0725 0.0069 0.9235
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