FX 60-177 AIRFOIL (fx60177-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 60-177 AIRFOIL (fx60177-il) Reynolds number: 200,000 Max Cl/Cd: 53.25 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60177-il-200000-n5.txt Download as CSV file: xf-fx60177-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-177 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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.6487 0.09899 0.09462 -0.0676 1.0001 0.0079
-15.250 -0.6861 0.08899 0.08434 -0.0720 1.0001 0.0078
-15.000 -0.7123 0.08207 0.07722 -0.0742 1.0001 0.0077
-14.750 -0.7333 0.07662 0.07158 -0.0753 1.0001 0.0077
-14.500 -0.7494 0.07181 0.06660 -0.0764 0.9998 0.0077
-14.250 -0.7542 0.06677 0.06136 -0.0796 0.9982 0.0077
-14.000 -0.7561 0.06246 0.05685 -0.0822 0.9965 0.0077
-13.750 -0.7555 0.05871 0.05292 -0.0845 0.9948 0.0078
-13.500 -0.7537 0.05544 0.04948 -0.0860 0.9929 0.0078
-13.250 -0.7503 0.05254 0.04642 -0.0872 0.9904 0.0079
-13.000 -0.7441 0.04991 0.04363 -0.0883 0.9880 0.0080
-12.750 -0.7358 0.04752 0.04109 -0.0894 0.9859 0.0081
-12.500 -0.7250 0.04532 0.03872 -0.0906 0.9842 0.0082
-12.250 -0.7167 0.04339 0.03667 -0.0906 0.9810 0.0083
-12.000 -0.7069 0.04159 0.03474 -0.0907 0.9776 0.0085
-11.750 -0.6944 0.03988 0.03290 -0.0911 0.9750 0.0087
-11.500 -0.6792 0.03824 0.03113 -0.0917 0.9730 0.0089
-11.250 -0.6645 0.03672 0.02949 -0.0921 0.9705 0.0092
-11.000 -0.6569 0.03544 0.02810 -0.0908 0.9655 0.0094
-10.750 -0.6427 0.03411 0.02663 -0.0907 0.9624 0.0097
-10.500 -0.6255 0.03279 0.02524 -0.0912 0.9601 0.0101
-10.250 -0.6050 0.03157 0.02395 -0.0922 0.9584 0.0107
-10.000 -0.6024 0.03073 0.02305 -0.0892 0.9513 0.0112
-9.750 -0.5867 0.02968 0.02191 -0.0890 0.9481 0.0120
-9.500 -0.5673 0.02859 0.02075 -0.0894 0.9458 0.0131
-9.250 -0.5575 0.02781 0.01991 -0.0876 0.9408 0.0143
-9.000 -0.5484 0.02708 0.01910 -0.0855 0.9352 0.0158
-8.750 -0.5303 0.02621 0.01820 -0.0853 0.9322 0.0179
-8.500 -0.5077 0.02539 0.01734 -0.0857 0.9302 0.0208
-8.250 -0.5133 0.02502 0.01694 -0.0805 0.9212 0.0224
-8.000 -0.4925 0.02430 0.01621 -0.0805 0.9181 0.0261
-7.750 -0.4673 0.02357 0.01547 -0.0812 0.9161 0.0316
-7.500 -0.4629 0.02318 0.01506 -0.0779 0.9091 0.0357
-7.250 -0.4433 0.02252 0.01440 -0.0775 0.9052 0.0419
-7.000 -0.4176 0.02178 0.01367 -0.0783 0.9029 0.0510
-6.500 -0.3857 0.02049 0.01256 -0.0764 0.8937 0.0850
-6.250 -0.3635 0.01961 0.01190 -0.0768 0.8902 0.1248
-6.000 -0.3354 0.01860 0.01115 -0.0784 0.8881 0.1813
-5.750 -0.3035 0.01715 0.01022 -0.0815 0.8866 0.2813
-5.500 -0.2653 0.01575 0.00944 -0.0858 0.8856 0.4125
-5.250 -0.2485 0.01550 0.00946 -0.0846 0.8781 0.4727
-5.000 -0.2168 0.01527 0.00938 -0.0856 0.8757 0.5188
-4.750 -0.1850 0.01520 0.00943 -0.0863 0.8738 0.5609
-4.500 -0.1527 0.01526 0.00953 -0.0868 0.8723 0.5917
-4.250 -0.1167 0.01525 0.00947 -0.0884 0.8711 0.6142
-4.000 -0.0996 0.01556 0.00976 -0.0864 0.8647 0.6267
-3.750 -0.0719 0.01569 0.00985 -0.0860 0.8610 0.6377
-3.500 -0.0378 0.01567 0.00977 -0.0871 0.8587 0.6488
-3.250 -0.0027 0.01565 0.00967 -0.0882 0.8569 0.6569
-3.000 0.0357 0.01551 0.00945 -0.0903 0.8555 0.6634
-2.750 0.0477 0.01577 0.00971 -0.0871 0.8465 0.6676
-2.500 0.0832 0.01561 0.00947 -0.0887 0.8437 0.6734
-2.250 0.1197 0.01548 0.00927 -0.0904 0.8417 0.6786
-2.000 0.1544 0.01546 0.00921 -0.0914 0.8400 0.6818
-1.750 0.1685 0.01564 0.00938 -0.0889 0.8312 0.6861
-1.500 0.2082 0.01534 0.00900 -0.0916 0.8280 0.6918
-1.250 0.2454 0.01517 0.00879 -0.0932 0.8252 0.6944
-1.000 0.2608 0.01534 0.00897 -0.0906 0.8165 0.6972
-0.750 0.2936 0.01524 0.00885 -0.0913 0.8120 0.7007
-0.500 0.3353 0.01502 0.00857 -0.0942 0.8091 0.7050
-0.250 0.3566 0.01500 0.00854 -0.0933 0.7998 0.7094
0.000 0.3912 0.01487 0.00839 -0.0944 0.7948 0.7111
0.250 0.4118 0.01492 0.00845 -0.0928 0.7852 0.7135
0.500 0.4496 0.01475 0.00824 -0.0946 0.7783 0.7162
0.750 0.4743 0.01472 0.00820 -0.0942 0.7670 0.7206
1.000 0.5105 0.01456 0.00799 -0.0961 0.7578 0.7248
1.250 0.5397 0.01452 0.00795 -0.0963 0.7482 0.7263
1.500 0.5636 0.01454 0.00796 -0.0954 0.7362 0.7281
1.750 0.5910 0.01453 0.00794 -0.0953 0.7234 0.7303
2.000 0.6202 0.01451 0.00789 -0.0956 0.7098 0.7329
2.250 0.6511 0.01448 0.00781 -0.0965 0.6947 0.7360
2.500 0.6863 0.01441 0.00767 -0.0984 0.6767 0.7400
2.750 0.7101 0.01451 0.00771 -0.0975 0.6572 0.7415
3.000 0.7332 0.01464 0.00778 -0.0965 0.6354 0.7433
3.250 0.7554 0.01481 0.00787 -0.0954 0.6118 0.7454
3.500 0.7778 0.01502 0.00796 -0.0944 0.5879 0.7477
3.750 0.7994 0.01525 0.00810 -0.0935 0.5613 0.7504
4.000 0.8227 0.01554 0.00824 -0.0931 0.5353 0.7538
4.250 0.8446 0.01586 0.00845 -0.0924 0.5104 0.7565
4.500 0.8618 0.01625 0.00875 -0.0906 0.4871 0.7580
4.750 0.8795 0.01665 0.00908 -0.0889 0.4648 0.7596
5.000 0.8979 0.01705 0.00942 -0.0875 0.4440 0.7615
5.250 0.9169 0.01746 0.00978 -0.0862 0.4244 0.7637
5.500 0.9367 0.01790 0.01016 -0.0852 0.4062 0.7664
5.750 0.9577 0.01835 0.01055 -0.0846 0.3864 0.7693
6.000 0.9792 0.01885 0.01096 -0.0842 0.3663 0.7721
6.250 0.9948 0.01936 0.01144 -0.0824 0.3492 0.7735
6.500 1.0115 0.01987 0.01192 -0.0809 0.3335 0.7751
6.750 1.0295 0.02036 0.01241 -0.0796 0.3188 0.7769
7.000 1.0472 0.02088 0.01293 -0.0783 0.3045 0.7791
7.250 1.0649 0.02146 0.01348 -0.0772 0.2901 0.7816
7.500 1.0836 0.02206 0.01405 -0.0763 0.2758 0.7842
7.750 1.1035 0.02268 0.01464 -0.0759 0.2622 0.7869
8.000 1.1206 0.02332 0.01528 -0.0747 0.2503 0.7889
8.250 1.1368 0.02390 0.01590 -0.0733 0.2403 0.7906
8.500 1.1528 0.02455 0.01657 -0.0719 0.2313 0.7924
8.750 1.1684 0.02527 0.01729 -0.0706 0.2214 0.7943
9.000 1.1858 0.02592 0.01800 -0.0697 0.2103 0.7964
9.250 1.2022 0.02668 0.01878 -0.0687 0.1997 0.7988
9.500 1.2180 0.02754 0.01962 -0.0678 0.1896 0.8014
9.750 1.2359 0.02834 0.02045 -0.0672 0.1809 0.8037
10.000 1.2478 0.02925 0.02138 -0.0656 0.1742 0.8052
10.250 1.2634 0.02999 0.02223 -0.0644 0.1666 0.8068
10.500 1.2753 0.03099 0.02325 -0.0630 0.1586 0.8085
10.750 1.2897 0.03188 0.02421 -0.0619 0.1489 0.8104
11.000 1.3022 0.03295 0.02529 -0.0607 0.1398 0.8124
11.250 1.3128 0.03419 0.02653 -0.0595 0.1316 0.8145
11.500 1.3267 0.03529 0.02769 -0.0588 0.1235 0.8169
11.750 1.3372 0.03668 0.02910 -0.0578 0.1158 0.8192
12.000 1.3477 0.03784 0.03034 -0.0565 0.1070 0.8209
12.250 1.3556 0.03926 0.03179 -0.0551 0.0993 0.8226
12.500 1.3632 0.04078 0.03335 -0.0538 0.0925 0.8244
12.750 1.3716 0.04232 0.03495 -0.0528 0.0874 0.8263
13.000 1.3804 0.04390 0.03662 -0.0519 0.0821 0.8283
13.250 1.3865 0.04578 0.03856 -0.0510 0.0776 0.8303
13.500 1.3957 0.04748 0.04038 -0.0504 0.0732 0.8324
13.750 1.4023 0.04950 0.04246 -0.0499 0.0684 0.8344
14.000 1.4056 0.05165 0.04469 -0.0490 0.0642 0.8360
14.250 1.4079 0.05395 0.04705 -0.0481 0.0593 0.8378
14.500 1.4075 0.05666 0.04981 -0.0474 0.0554 0.8397
14.750 1.4113 0.05900 0.05228 -0.0470 0.0515 0.8418
15.000 1.4128 0.06172 0.05509 -0.0467 0.0478 0.8439
15.250 1.4123 0.06478 0.05823 -0.0467 0.0442 0.8459
15.500 1.4135 0.06777 0.06133 -0.0469 0.0408 0.8479
15.750 1.4121 0.07120 0.06486 -0.0473 0.0379 0.8498
16.000 1.4088 0.07467 0.06845 -0.0475 0.0358 0.8514
16.250 1.4050 0.07831 0.07222 -0.0479 0.0337 0.8531
16.500 1.3992 0.08235 0.07637 -0.0486 0.0318 0.8549
16.750 1.3904 0.08696 0.08107 -0.0496 0.0297 0.8567
17.000 1.3860 0.09106 0.08533 -0.0507 0.0276 0.8586
17.250 1.3792 0.09562 0.09003 -0.0521 0.0256 0.8604
17.500 1.3707 0.10057 0.09510 -0.0539 0.0241 0.8621
17.750 1.3636 0.10541 0.10010 -0.0558 0.0225 0.8638
18.000 1.3557 0.11041 0.10526 -0.0578 0.0201 0.8654
18.250 1.3433 0.11608 0.11105 -0.0602 0.0175 0.8668
18.750 1.3139 0.12858 0.12380 -0.0661 0.0139 0.8698
19.000 1.2976 0.13539 0.13072 -0.0697 0.0124 0.8714
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