FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-158 AIRFOIL (fx63158-il) Reynolds number: 200,000 Max Cl/Cd: 72.38 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63158-il-200000.txt Download as CSV file: xf-fx63158-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-158 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2258 0.09139 0.08855 -0.0544 0.9932 0.0445
-9.500 -0.2343 0.08247 0.07965 -0.0626 0.9887 0.0461
-8.750 -0.3316 0.07877 0.07586 -0.0626 0.9930 0.0430
-8.500 -0.3301 0.07004 0.06703 -0.0751 0.9837 0.0438
-8.250 -0.3373 0.06355 0.06040 -0.0836 0.9646 0.0446
-7.750 -0.3224 0.05175 0.04805 -0.0978 0.9304 0.0482
-7.250 -0.2661 0.04399 0.03986 -0.1076 0.9077 0.0577
-7.000 -0.2304 0.04039 0.03598 -0.1134 0.8933 0.0662
-6.750 -0.1886 0.03711 0.03242 -0.1198 0.8784 0.0776
-6.500 -0.1501 0.03445 0.02931 -0.1256 0.8581 0.0965
-6.250 -0.1160 0.03174 0.02642 -0.1289 0.8372 0.1092
-6.000 -0.0862 0.02982 0.02427 -0.1309 0.8167 0.1244
-5.750 -0.0330 0.01098 0.00371 -0.1219 0.7775 0.0344
-5.500 -0.0061 0.00987 0.00208 -0.1213 0.7651 0.0301
-5.250 0.0184 0.02058 0.01257 -0.1257 0.7723 0.0293
-5.000 0.0431 0.01957 0.01145 -0.1246 0.7584 0.0289
-4.750 0.0685 0.01890 0.01060 -0.1237 0.7459 0.0296
-4.500 0.0929 0.01815 0.00984 -0.1230 0.7346 0.0320
-4.250 0.1159 0.01758 0.00921 -0.1219 0.7228 0.0331
-4.000 0.1398 0.01702 0.00859 -0.1211 0.7120 0.0336
-3.750 0.1651 0.01654 0.00800 -0.1207 0.7014 0.0346
-3.500 0.1901 0.01582 0.00728 -0.1209 0.6908 0.0364
-3.250 0.2190 0.01533 0.00661 -0.1216 0.6818 0.0400
-3.000 0.2502 0.01423 0.00568 -0.1233 0.6721 0.1054
-2.750 0.2844 0.01292 0.00632 -0.1262 0.6643 0.6094
-2.500 0.3119 0.01336 0.00664 -0.1257 0.6562 0.6402
-2.250 0.3340 0.01418 0.00736 -0.1234 0.6499 0.6611
-2.000 0.3564 0.01471 0.00786 -0.1215 0.6422 0.6752
-1.750 0.3809 0.01503 0.00807 -0.1203 0.6346 0.6840
-1.500 0.4068 0.01521 0.00814 -0.1197 0.6270 0.6905
-1.250 0.4283 0.01548 0.00836 -0.1178 0.6193 0.6959
-1.000 0.4565 0.01570 0.00842 -0.1179 0.6123 0.7058
-0.750 0.4751 0.01596 0.00870 -0.1152 0.6055 0.7105
-0.500 0.5001 0.01613 0.00878 -0.1144 0.6001 0.7159
-0.250 0.5316 0.01621 0.00875 -0.1155 0.5953 0.7232
0.000 0.5519 0.01636 0.00894 -0.1135 0.5902 0.7269
0.250 0.5748 0.01653 0.00908 -0.1122 0.5852 0.7328
0.500 0.6037 0.01667 0.00912 -0.1126 0.5808 0.7411
0.750 0.6202 0.01688 0.00938 -0.1095 0.5764 0.7472
1.000 0.6466 0.01703 0.00953 -0.1093 0.5714 0.7576
1.250 0.6609 0.01717 0.00971 -0.1056 0.5673 0.7645
1.500 0.6913 0.01734 0.00978 -0.1064 0.5632 0.7743
1.750 0.7066 0.01734 0.00985 -0.1033 0.5587 0.7791
2.000 0.7303 0.01737 0.00991 -0.1025 0.5539 0.7847
2.250 0.7632 0.01743 0.00991 -0.1041 0.5491 0.7901
2.500 0.7903 0.01742 0.00985 -0.1042 0.5449 0.7928
2.750 0.8135 0.01738 0.00987 -0.1035 0.5399 0.7951
3.000 0.8389 0.01738 0.00991 -0.1032 0.5350 0.7978
3.250 0.8670 0.01741 0.00991 -0.1036 0.5306 0.8007
3.500 0.8967 0.01747 0.00997 -0.1044 0.5260 0.8034
3.750 0.9267 0.01750 0.01006 -0.1055 0.5202 0.8059
4.000 0.9589 0.01755 0.01012 -0.1070 0.5146 0.8079
4.250 0.9845 0.01753 0.01011 -0.1068 0.5096 0.8096
4.500 1.0073 0.01749 0.01017 -0.1060 0.5033 0.8117
4.750 1.0327 0.01750 0.01022 -0.1058 0.4981 0.8139
5.000 1.0602 0.01756 0.01029 -0.1060 0.4936 0.8160
5.250 1.0869 0.01763 0.01046 -0.1063 0.4879 0.8182
5.500 1.1151 0.01770 0.01059 -0.1068 0.4824 0.8202
5.750 1.1452 0.01781 0.01067 -0.1077 0.4777 0.8217
6.000 1.1731 0.01793 0.01093 -0.1083 0.4715 0.8231
6.250 1.2017 0.01804 0.01111 -0.1090 0.4646 0.8244
6.500 1.2286 0.01814 0.01126 -0.1093 0.4576 0.8257
6.750 1.2516 0.01818 0.01144 -0.1088 0.4488 0.8271
7.000 1.2742 0.01825 0.01160 -0.1081 0.4399 0.8289
7.250 1.2966 0.01833 0.01175 -0.1074 0.4301 0.8309
7.500 1.3200 0.01848 0.01198 -0.1070 0.4213 0.8325
7.750 1.3433 0.01867 0.01221 -0.1066 0.4130 0.8341
8.000 1.3667 0.01891 0.01256 -0.1063 0.4035 0.8357
8.250 1.3883 0.01918 0.01289 -0.1057 0.3923 0.8373
8.500 1.4090 0.01947 0.01329 -0.1049 0.3766 0.8390
8.750 1.4259 0.01983 0.01366 -0.1035 0.3600 0.8407
9.000 1.4400 0.02033 0.01413 -0.1017 0.3461 0.8423
9.250 1.4524 0.02085 0.01471 -0.0996 0.3288 0.8439
9.500 1.4618 0.02151 0.01540 -0.0971 0.3036 0.8458
9.750 1.4627 0.02258 0.01635 -0.0935 0.2848 0.8480
10.000 1.4695 0.02356 0.01738 -0.0910 0.2578 0.8506
10.250 1.4633 0.02527 0.01894 -0.0872 0.2331 0.8532
10.500 1.4613 0.02702 0.02066 -0.0845 0.2100 0.8557
10.750 1.4525 0.02943 0.02293 -0.0817 0.1826 0.8578
11.000 1.4457 0.03194 0.02542 -0.0795 0.1674 0.8600
11.250 1.4405 0.03442 0.02789 -0.0777 0.1415 0.8626
11.500 1.4290 0.03772 0.03111 -0.0761 0.1312 0.8652
11.750 1.4242 0.04074 0.03420 -0.0752 0.1207 0.8677
12.000 1.4257 0.04334 0.03687 -0.0748 0.1033 0.8702
12.250 1.4184 0.04697 0.04043 -0.0746 0.0959 0.8725
12.500 1.4102 0.05088 0.04434 -0.0745 0.0912 0.8748
12.750 1.4031 0.05471 0.04824 -0.0745 0.0869 0.8769
13.000 1.3994 0.05813 0.05180 -0.0745 0.0821 0.8794
13.250 1.3996 0.06123 0.05504 -0.0746 0.0769 0.8822
13.500 1.4032 0.06403 0.05797 -0.0748 0.0707 0.8854
13.750 1.4055 0.06711 0.06112 -0.0753 0.0664 0.8888
14.000 1.4041 0.07078 0.06481 -0.0760 0.0635 0.8921
14.250 1.4000 0.07460 0.06868 -0.0765 0.0612 0.8957
14.500 1.3938 0.07873 0.07280 -0.0770 0.0591 0.8996
14.750 1.3912 0.08246 0.07659 -0.0775 0.0568 0.9039
15.000 1.3918 0.08588 0.08010 -0.0781 0.0544 0.9086
15.250 1.3922 0.08886 0.08307 -0.0781 0.0522 0.9139
15.500 1.3962 0.09143 0.08572 -0.0781 0.0500 0.9213
15.750 1.3978 0.09448 0.08898 -0.0786 0.0480 0.9335
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