FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: FX 61-168 AIRFOIL (fx61168-il) Reynolds number: 200,000 Max Cl/Cd: 73 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61168-il-200000-n5.txt Download as CSV file: xf-fx61168-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-168 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4298 0.08886 0.08530 -0.0586 1.0000 0.0113
-11.750 -0.4698 0.07608 0.07235 -0.0666 1.0000 0.0114
-11.500 -0.4752 0.07268 0.06897 -0.0680 1.0000 0.0111
-11.250 -0.5145 0.06448 0.06053 -0.0718 1.0000 0.0113
-11.000 -0.5230 0.06165 0.05771 -0.0720 1.0000 0.0111
-10.750 -0.5475 0.05735 0.05328 -0.0719 1.0000 0.0111
-10.500 -0.5600 0.05127 0.04686 -0.0764 0.9931 0.0112
-10.250 -0.5676 0.04660 0.04183 -0.0791 0.9770 0.0113
-9.750 -0.5678 0.03960 0.03425 -0.0815 0.9270 0.0116
-9.500 -0.5428 0.03611 0.03042 -0.0856 0.9080 0.0118
-9.250 -0.5066 0.03293 0.02685 -0.0907 0.8909 0.0121
-9.000 -0.4616 0.03008 0.02359 -0.0966 0.8721 0.0125
-8.750 -0.4158 0.02768 0.02081 -0.1018 0.8512 0.0131
-8.500 -0.3736 0.02576 0.01852 -0.1055 0.8299 0.0138
-8.250 -0.3384 0.02435 0.01681 -0.1074 0.8091 0.0145
-8.000 -0.3105 0.02332 0.01555 -0.1080 0.7901 0.0156
-7.750 -0.2876 0.02259 0.01472 -0.1080 0.7734 0.0166
-7.500 -0.2659 0.02184 0.01383 -0.1074 0.7593 0.0175
-7.250 -0.2459 0.02107 0.01293 -0.1065 0.7474 0.0184
-7.000 -0.2271 0.02037 0.01210 -0.1055 0.7370 0.0190
-6.750 -0.2101 0.01963 0.01126 -0.1043 0.7274 0.0200
-6.500 -0.1932 0.01892 0.01046 -0.1034 0.7190 0.0211
-6.250 -0.1736 0.01840 0.00988 -0.1027 0.7109 0.0234
-6.000 -0.1528 0.01791 0.00925 -0.1021 0.7041 0.0256
-5.750 -0.1333 0.01724 0.00855 -0.1016 0.6975 0.0284
-5.500 -0.1105 0.01678 0.00796 -0.1013 0.6919 0.0323
-5.250 -0.0876 0.01624 0.00739 -0.1012 0.6867 0.0401
-5.000 -0.0641 0.01568 0.00685 -0.1011 0.6812 0.0558
-4.750 -0.0408 0.01485 0.00626 -0.1016 0.6765 0.1161
-4.500 -0.0175 0.01288 0.00537 -0.1039 0.6717 0.3615
-4.250 0.0098 0.01235 0.00543 -0.1045 0.6670 0.5041
-4.000 0.0368 0.01261 0.00582 -0.1039 0.6630 0.5645
-3.750 0.0643 0.01309 0.00626 -0.1033 0.6593 0.5980
-3.500 0.0917 0.01349 0.00659 -0.1028 0.6549 0.6157
-3.250 0.1204 0.01360 0.00657 -0.1030 0.6506 0.6239
-3.000 0.1485 0.01371 0.00657 -0.1030 0.6467 0.6278
-2.750 0.1782 0.01376 0.00647 -0.1035 0.6432 0.6334
-2.500 0.2069 0.01377 0.00639 -0.1038 0.6388 0.6381
-2.250 0.2344 0.01387 0.00643 -0.1037 0.6348 0.6412
-2.000 0.2629 0.01394 0.00641 -0.1039 0.6313 0.6452
-1.750 0.2941 0.01397 0.00626 -0.1049 0.6282 0.6513
-1.500 0.3207 0.01407 0.00638 -0.1046 0.6243 0.6544
-1.250 0.3478 0.01419 0.00646 -0.1044 0.6205 0.6580
-1.000 0.3767 0.01426 0.00646 -0.1048 0.6170 0.6625
-0.750 0.4077 0.01428 0.00635 -0.1058 0.6137 0.6673
-0.500 0.4343 0.01434 0.00642 -0.1056 0.6095 0.6694
-0.250 0.4615 0.01441 0.00648 -0.1055 0.6052 0.6719
0.000 0.4897 0.01447 0.00650 -0.1057 0.6014 0.6749
0.250 0.5194 0.01453 0.00648 -0.1063 0.5983 0.6784
0.500 0.5494 0.01455 0.00646 -0.1071 0.5945 0.6823
0.750 0.5759 0.01461 0.00657 -0.1069 0.5905 0.6842
1.000 0.6034 0.01469 0.00664 -0.1069 0.5869 0.6864
1.250 0.6317 0.01476 0.00669 -0.1072 0.5837 0.6888
1.500 0.6600 0.01484 0.00676 -0.1075 0.5800 0.6918
1.750 0.6885 0.01488 0.00683 -0.1079 0.5754 0.6952
2.000 0.7172 0.01493 0.00686 -0.1083 0.5710 0.6979
2.250 0.7448 0.01500 0.00692 -0.1084 0.5673 0.6996
2.500 0.7708 0.01508 0.00707 -0.1082 0.5624 0.7018
2.750 0.7978 0.01515 0.00719 -0.1082 0.5578 0.7043
3.000 0.8259 0.01522 0.00726 -0.1084 0.5538 0.7069
3.250 0.8543 0.01530 0.00736 -0.1088 0.5495 0.7097
3.500 0.8824 0.01538 0.00750 -0.1092 0.5446 0.7126
3.750 0.9085 0.01546 0.00763 -0.1090 0.5400 0.7144
4.000 0.9352 0.01555 0.00775 -0.1089 0.5354 0.7164
4.250 0.9606 0.01563 0.00793 -0.1086 0.5289 0.7185
4.500 0.9873 0.01570 0.00803 -0.1086 0.5233 0.7210
4.750 1.0140 0.01581 0.00821 -0.1086 0.5174 0.7237
5.000 1.0410 0.01590 0.00836 -0.1088 0.5110 0.7265
5.250 1.0669 0.01599 0.00849 -0.1086 0.5048 0.7285
5.500 1.0909 0.01609 0.00871 -0.1080 0.4968 0.7304
5.750 1.1155 0.01619 0.00886 -0.1076 0.4892 0.7326
6.000 1.1395 0.01630 0.00904 -0.1071 0.4799 0.7349
6.250 1.1637 0.01644 0.00924 -0.1066 0.4704 0.7373
6.500 1.1879 0.01659 0.00943 -0.1062 0.4608 0.7399
6.750 1.2118 0.01677 0.00967 -0.1058 0.4502 0.7426
7.000 1.2334 0.01696 0.00994 -0.1048 0.4393 0.7444
7.250 1.2544 0.01719 0.01021 -0.1038 0.4280 0.7462
7.500 1.2745 0.01746 0.01052 -0.1026 0.4162 0.7485
7.750 1.2946 0.01776 0.01088 -0.1015 0.4048 0.7510
8.000 1.3140 0.01810 0.01127 -0.1003 0.3923 0.7536
8.250 1.3315 0.01851 0.01169 -0.0988 0.3776 0.7561
8.750 1.3571 0.01942 0.01266 -0.0942 0.3475 0.7603
9.000 1.3677 0.02000 0.01325 -0.0916 0.3317 0.7628
9.250 1.3755 0.02072 0.01397 -0.0888 0.3132 0.7655
9.500 1.3821 0.02156 0.01479 -0.0859 0.2927 0.7683
9.750 1.3852 0.02262 0.01579 -0.0828 0.2716 0.7710
10.000 1.3861 0.02384 0.01697 -0.0797 0.2491 0.7734
10.250 1.3840 0.02531 0.01840 -0.0765 0.2284 0.7757
10.500 1.3816 0.02699 0.02006 -0.0737 0.2085 0.7784
10.750 1.3779 0.02895 0.02198 -0.0713 0.1882 0.7814
11.000 1.3734 0.03121 0.02419 -0.0692 0.1706 0.7846
11.250 1.3707 0.03356 0.02650 -0.0677 0.1539 0.7876
11.500 1.3672 0.03603 0.02897 -0.0663 0.1374 0.7899
11.750 1.3651 0.03856 0.03150 -0.0652 0.1244 0.7926
12.000 1.3638 0.04113 0.03409 -0.0644 0.1118 0.7954
12.250 1.3628 0.04380 0.03677 -0.0638 0.1001 0.7984
12.500 1.3627 0.04647 0.03948 -0.0634 0.0902 0.8015
12.750 1.3626 0.04915 0.04221 -0.0629 0.0807 0.8044
13.000 1.3607 0.05208 0.04517 -0.0626 0.0709 0.8076
13.250 1.3576 0.05526 0.04836 -0.0624 0.0613 0.8111
13.500 1.3542 0.05859 0.05172 -0.0624 0.0535 0.8148
13.750 1.3538 0.06167 0.05487 -0.0625 0.0465 0.8184
14.000 1.3516 0.06500 0.05825 -0.0626 0.0404 0.8220
14.250 1.3503 0.06834 0.06165 -0.0630 0.0356 0.8260
14.500 1.3494 0.07175 0.06513 -0.0634 0.0320 0.8304
14.750 1.3488 0.07514 0.06863 -0.0639 0.0288 0.8350
15.000 1.3459 0.07890 0.07246 -0.0646 0.0258 0.8401
15.250 1.3462 0.08233 0.07602 -0.0652 0.0227 0.8462
15.500 1.3433 0.08616 0.07995 -0.0660 0.0201 0.8527
15.750 1.3420 0.08984 0.08377 -0.0668 0.0178 0.8613
16.000 1.3384 0.09371 0.08776 -0.0675 0.0156 0.8722
16.250 1.3335 0.09757 0.09176 -0.0681 0.0137 0.8894
16.500 1.3238 0.10080 0.09515 -0.0675 0.0124 1.0000
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