FX 84-W-175 (fx84w175-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-175 (fx84w175-il) Reynolds number: 200,000 Max Cl/Cd: 68.36 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w175-il-200000.txt Download as CSV file: xf-fx84w175-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-175
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1149 0.10670 0.10287 -0.1074 0.9455 0.0818
-12.000 -0.3351 0.05812 0.05390 -0.1391 0.9326 0.0543
-11.750 -0.3607 0.05325 0.04887 -0.1410 0.9222 0.0540
-11.500 -0.3865 0.04953 0.04495 -0.1409 0.9119 0.0538
-11.250 -0.4130 0.04643 0.04165 -0.1392 0.9007 0.0536
-11.000 -0.4393 0.04394 0.03889 -0.1357 0.8915 0.0536
-10.750 -0.4608 0.04182 0.03649 -0.1317 0.8822 0.0537
-10.500 -0.4756 0.03963 0.03389 -0.1279 0.8758 0.0541
-10.250 -0.4807 0.03737 0.03131 -0.1253 0.8678 0.0548
-10.000 -0.4657 0.03593 0.02985 -0.1243 0.8630 0.0559
-9.750 -0.4485 0.03503 0.02891 -0.1231 0.8595 0.0571
-9.500 -0.4379 0.03377 0.02750 -0.1217 0.8526 0.0582
-9.250 -0.4271 0.03220 0.02564 -0.1200 0.8472 0.0593
-9.000 -0.4143 0.03066 0.02374 -0.1181 0.8433 0.0607
-8.750 -0.4017 0.02963 0.02235 -0.1164 0.8377 0.0621
-8.500 -0.3807 0.02836 0.02115 -0.1160 0.8326 0.0640
-8.250 -0.3593 0.02758 0.02028 -0.1152 0.8285 0.0659
-8.000 -0.3374 0.02663 0.01914 -0.1143 0.8253 0.0681
-7.750 -0.3181 0.02599 0.01825 -0.1132 0.8201 0.0703
-7.500 -0.2961 0.02493 0.01725 -0.1127 0.8149 0.0729
-7.250 -0.2724 0.02435 0.01662 -0.1122 0.8110 0.0759
-7.000 -0.2478 0.02366 0.01575 -0.1116 0.8079 0.0791
-6.750 -0.2248 0.02283 0.01489 -0.1110 0.8039 0.0824
-6.500 -0.2033 0.02249 0.01460 -0.1103 0.7980 0.0863
-6.250 -0.1788 0.02207 0.01402 -0.1097 0.7940 0.0908
-6.000 -0.1537 0.02122 0.01324 -0.1093 0.7910 0.0959
-5.750 -0.1273 0.02079 0.01270 -0.1089 0.7884 0.1020
-5.500 -0.1087 0.02042 0.01244 -0.1079 0.7816 0.1078
-5.250 -0.0843 0.02011 0.01208 -0.1074 0.7774 0.1154
-5.000 -0.0593 0.01950 0.01152 -0.1069 0.7742 0.1241
-4.750 -0.0329 0.01898 0.01097 -0.1066 0.7716 0.1348
-4.500 -0.0125 0.01892 0.01093 -0.1057 0.7656 0.1460
-4.250 0.0099 0.01856 0.01067 -0.1050 0.7610 0.1602
-4.000 0.0356 0.01812 0.01026 -0.1047 0.7576 0.1786
-3.750 0.0618 0.01757 0.00982 -0.1045 0.7549 0.2028
-3.500 0.0833 0.01735 0.00973 -0.1037 0.7501 0.2336
-3.250 0.1035 0.01703 0.00966 -0.1028 0.7447 0.2764
-3.000 0.1270 0.01645 0.00939 -0.1023 0.7411 0.3486
-2.750 0.1511 0.01576 0.00913 -0.1018 0.7383 0.4586
-2.500 0.1746 0.01541 0.00915 -0.1008 0.7351 0.5621
-2.250 0.1922 0.01558 0.00956 -0.0990 0.7286 0.6247
-2.000 0.2176 0.01558 0.00963 -0.0981 0.7248 0.6722
-1.750 0.2456 0.01554 0.00959 -0.0976 0.7219 0.7068
-1.500 0.2748 0.01552 0.00954 -0.0972 0.7194 0.7344
-1.250 0.2918 0.01593 0.01001 -0.0952 0.7130 0.7556
-1.000 0.3156 0.01608 0.01015 -0.0940 0.7086 0.7752
-0.750 0.3427 0.01609 0.01011 -0.0932 0.7054 0.7931
-0.500 0.3710 0.01607 0.01002 -0.0926 0.7029 0.8096
-0.250 0.3884 0.01641 0.01039 -0.0906 0.6973 0.8252
0.000 0.4083 0.01659 0.01058 -0.0888 0.6923 0.8396
0.250 0.4329 0.01658 0.01053 -0.0874 0.6889 0.8525
0.500 0.4599 0.01650 0.01038 -0.0866 0.6862 0.8656
0.750 0.4765 0.01673 0.01063 -0.0843 0.6813 0.8799
1.000 0.4909 0.01692 0.01084 -0.0815 0.6758 0.8954
1.250 0.5128 0.01686 0.01075 -0.0796 0.6723 0.9112
1.500 0.5429 0.01672 0.01054 -0.0792 0.6695 0.9237
1.750 0.5699 0.01683 0.01064 -0.0791 0.6653 0.9341
2.000 0.5931 0.01703 0.01086 -0.0786 0.6594 0.9451
2.250 0.6330 0.01695 0.01073 -0.0809 0.6557 0.9521
2.500 0.6759 0.01681 0.01051 -0.0838 0.6528 0.9581
2.750 0.7192 0.01691 0.01057 -0.0871 0.6488 0.9630
3.000 0.7527 0.01714 0.01085 -0.0890 0.6427 0.9707
3.250 0.8004 0.01707 0.01073 -0.0931 0.6387 0.9740
3.500 0.8472 0.01693 0.01051 -0.0969 0.6356 0.9781
3.750 0.8851 0.01712 0.01073 -0.0996 0.6303 0.9841
4.000 0.9249 0.01724 0.01088 -0.1026 0.6247 0.9900
4.250 0.9680 0.01713 0.01074 -0.1060 0.6207 0.9947
4.500 1.0146 0.01697 0.01049 -0.1098 0.6174 0.9983
4.750 1.0155 0.01742 0.01107 -0.1059 0.6106 1.0000
5.000 1.0255 0.01750 0.01114 -0.1031 0.6058 1.0000
5.250 1.0491 0.01740 0.01098 -0.1024 0.6021 1.0000
5.500 1.0494 0.01770 0.01133 -0.0980 0.5968 1.0000
5.750 1.0568 0.01795 0.01161 -0.0948 0.5910 1.0000
6.000 1.0862 0.01791 0.01152 -0.0952 0.5867 1.0000
6.250 1.1158 0.01798 0.01156 -0.0957 0.5824 1.0000
6.500 1.1260 0.01840 0.01207 -0.0932 0.5753 1.0000
6.750 1.1567 0.01836 0.01200 -0.0939 0.5703 1.0000
7.000 1.1871 0.01842 0.01204 -0.0945 0.5655 1.0000
7.250 1.1983 0.01883 0.01254 -0.0921 0.5583 1.0000
7.500 1.2305 0.01878 0.01245 -0.0929 0.5531 1.0000
7.750 1.2523 0.01902 0.01272 -0.0922 0.5471 1.0000
8.000 1.2683 0.01930 0.01307 -0.0905 0.5402 1.0000
8.250 1.3042 0.01921 0.01292 -0.0919 0.5350 1.0000
8.500 1.3118 0.01969 0.01351 -0.0890 0.5277 1.0000
8.750 1.3360 0.01977 0.01361 -0.0885 0.5210 1.0000
9.000 1.3586 0.01996 0.01380 -0.0879 0.5145 1.0000
9.250 1.3656 0.02027 0.01417 -0.0846 0.5064 1.0000
9.500 1.3871 0.02029 0.01417 -0.0836 0.4982 1.0000
9.750 1.3894 0.02065 0.01458 -0.0797 0.4887 1.0000
10.000 1.3986 0.02099 0.01493 -0.0771 0.4792 1.0000
10.250 1.4116 0.02126 0.01519 -0.0750 0.4698 1.0000
10.500 1.4126 0.02200 0.01601 -0.0716 0.4601 1.0000
10.750 1.4324 0.02221 0.01616 -0.0706 0.4508 1.0000
11.000 1.4269 0.02330 0.01736 -0.0666 0.4406 1.0000
11.250 1.4361 0.02397 0.01804 -0.0646 0.4306 1.0000
11.500 1.4442 0.02470 0.01876 -0.0625 0.4199 1.0000
11.750 1.4427 0.02596 0.02011 -0.0595 0.4086 1.0000
12.000 1.4472 0.02702 0.02118 -0.0573 0.3970 1.0000
12.250 1.4521 0.02810 0.02223 -0.0552 0.3847 1.0000
12.500 1.4522 0.02954 0.02370 -0.0529 0.3717 1.0000
12.750 1.4504 0.03119 0.02538 -0.0506 0.3579 1.0000
13.000 1.4494 0.03293 0.02713 -0.0485 0.3439 1.0000
13.250 1.4478 0.03481 0.02900 -0.0466 0.3292 1.0000
13.500 1.4455 0.03686 0.03104 -0.0448 0.3139 1.0000
13.750 1.4420 0.03913 0.03328 -0.0431 0.2979 1.0000
14.000 1.4373 0.04161 0.03573 -0.0415 0.2813 1.0000
14.250 1.4317 0.04430 0.03838 -0.0400 0.2644 1.0000
14.500 1.4248 0.04724 0.04126 -0.0387 0.2472 1.0000
14.750 1.4171 0.05038 0.04434 -0.0376 0.2303 1.0000
15.000 1.4081 0.05379 0.04769 -0.0367 0.2133 1.0000
15.250 1.3995 0.05732 0.05117 -0.0359 0.1964 1.0000
15.500 1.3905 0.06101 0.05482 -0.0354 0.1794 1.0000
15.750 1.3807 0.06493 0.05868 -0.0350 0.1630 1.0000
16.000 1.3708 0.06899 0.06268 -0.0349 0.1476 1.0000
16.250 1.3612 0.07312 0.06675 -0.0349 0.1341 1.0000
16.500 1.3527 0.07723 0.07081 -0.0350 0.1223 1.0000
16.750 1.3447 0.08135 0.07487 -0.0353 0.1126 1.0000
17.000 1.3388 0.08529 0.07879 -0.0357 0.1037 1.0000
17.250 1.3356 0.08895 0.08248 -0.0361 0.0960 1.0000
17.500 1.3307 0.09279 0.08625 -0.0367 0.0898 1.0000
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