FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-158 AIRFOIL (fx63158-il) Reynolds number: 200,000 Max Cl/Cd: 67.88 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63158-il-200000-n5.txt Download as CSV file: xf-fx63158-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3302 0.05602 0.05227 -0.0897 0.9262 0.0144
-8.500 -0.3242 0.05182 0.04791 -0.0947 0.9054 0.0141
-8.000 -0.2889 0.03808 0.03286 -0.1094 0.8657 0.0115
-7.750 -0.2539 0.03459 0.02899 -0.1147 0.8422 0.0114
-7.500 -0.2221 0.03140 0.02533 -0.1184 0.8183 0.0113
-7.250 -0.1952 0.02893 0.02241 -0.1200 0.7944 0.0112
-7.000 -0.1703 0.02694 0.02000 -0.1206 0.7732 0.0111
-6.500 -0.1237 0.02372 0.01603 -0.1199 0.7370 0.0111
-6.250 -0.1001 0.02241 0.01443 -0.1192 0.7229 0.0113
-6.000 -0.0765 0.02132 0.01309 -0.1184 0.7104 0.0114
-5.750 -0.0531 0.02038 0.01198 -0.1176 0.6987 0.0117
-5.500 -0.0302 0.01962 0.01114 -0.1168 0.6877 0.0120
-5.250 -0.0068 0.01899 0.01042 -0.1162 0.6781 0.0126
-5.000 0.0171 0.01847 0.00978 -0.1157 0.6695 0.0138
-4.750 0.0410 0.01794 0.00914 -0.1152 0.6606 0.0151
-4.500 0.0644 0.01735 0.00850 -0.1148 0.6508 0.0159
-4.250 0.0891 0.01677 0.00786 -0.1147 0.6416 0.0164
-3.750 0.1417 0.01583 0.00667 -0.1151 0.6222 0.0178
-3.500 0.1692 0.01541 0.00609 -0.1156 0.6132 0.0190
-3.250 0.1974 0.01507 0.00564 -0.1161 0.6040 0.0209
-3.000 0.2260 0.01477 0.00529 -0.1166 0.5957 0.0256
-2.750 0.2553 0.01450 0.00493 -0.1172 0.5873 0.0439
-2.500 0.2869 0.01393 0.00460 -0.1189 0.5801 0.1371
-2.250 0.3286 0.01244 0.00423 -0.1241 0.5727 0.4430
-2.000 0.3533 0.01256 0.00488 -0.1231 0.5653 0.5790
-1.750 0.3807 0.01274 0.00500 -0.1229 0.5575 0.6054
-1.500 0.4102 0.01284 0.00491 -0.1234 0.5490 0.6201
-1.250 0.4379 0.01299 0.00496 -0.1233 0.5409 0.6318
-1.000 0.4649 0.01318 0.00507 -0.1231 0.5330 0.6423
-0.750 0.4934 0.01335 0.00511 -0.1233 0.5269 0.6522
-0.500 0.5211 0.01346 0.00519 -0.1232 0.5212 0.6569
-0.250 0.5480 0.01359 0.00528 -0.1230 0.5154 0.6612
0.000 0.5764 0.01372 0.00533 -0.1232 0.5104 0.6669
0.250 0.6046 0.01384 0.00543 -0.1233 0.5052 0.6732
0.500 0.6297 0.01404 0.00563 -0.1226 0.5003 0.6793
0.750 0.6580 0.01423 0.00575 -0.1227 0.4955 0.6887
1.000 0.6803 0.01447 0.00605 -0.1213 0.4909 0.6949
1.250 0.7078 0.01467 0.00621 -0.1212 0.4861 0.7034
1.500 0.7326 0.01482 0.00636 -0.1205 0.4816 0.7078
1.750 0.7572 0.01497 0.00650 -0.1199 0.4773 0.7110
2.000 0.7843 0.01506 0.00661 -0.1198 0.4722 0.7140
2.250 0.8120 0.01516 0.00670 -0.1200 0.4663 0.7172
2.500 0.8404 0.01527 0.00675 -0.1204 0.4606 0.7203
2.750 0.8701 0.01533 0.00684 -0.1211 0.4544 0.7227
3.000 0.8964 0.01541 0.00695 -0.1210 0.4473 0.7239
3.250 0.9226 0.01550 0.00706 -0.1209 0.4405 0.7253
3.500 0.9489 0.01561 0.00719 -0.1207 0.4332 0.7268
3.750 0.9747 0.01573 0.00733 -0.1206 0.4261 0.7285
4.000 1.0002 0.01588 0.00746 -0.1204 0.4172 0.7303
4.250 1.0256 0.01605 0.00760 -0.1202 0.4080 0.7319
4.500 1.0516 0.01622 0.00777 -0.1202 0.3977 0.7335
4.750 1.0783 0.01638 0.00797 -0.1203 0.3891 0.7350
5.000 1.1048 0.01656 0.00818 -0.1204 0.3768 0.7369
5.250 1.1300 0.01681 0.00840 -0.1203 0.3636 0.7388
5.500 1.1530 0.01709 0.00866 -0.1198 0.3527 0.7401
5.750 1.1753 0.01738 0.00894 -0.1190 0.3433 0.7412
6.000 1.1981 0.01765 0.00925 -0.1184 0.3320 0.7423
6.250 1.2194 0.01800 0.00962 -0.1176 0.3098 0.7435
6.500 1.2350 0.01860 0.01010 -0.1158 0.2900 0.7448
6.750 1.2533 0.01909 0.01057 -0.1146 0.2751 0.7462
7.000 1.2688 0.01969 0.01114 -0.1129 0.2455 0.7476
7.250 1.2787 0.02046 0.01180 -0.1103 0.2294 0.7492
7.500 1.2946 0.02100 0.01237 -0.1087 0.2183 0.7507
7.750 1.3133 0.02145 0.01290 -0.1076 0.2013 0.7523
8.000 1.3220 0.02240 0.01377 -0.1051 0.1844 0.7540
8.250 1.3348 0.02317 0.01456 -0.1033 0.1782 0.7559
8.500 1.3447 0.02403 0.01545 -0.1011 0.1721 0.7575
8.750 1.3601 0.02461 0.01617 -0.0996 0.1630 0.7590
9.000 1.3679 0.02564 0.01724 -0.0974 0.1418 0.7606
9.250 1.3709 0.02701 0.01859 -0.0948 0.1337 0.7621
9.500 1.3764 0.02832 0.01995 -0.0927 0.1289 0.7639
9.750 1.3843 0.02956 0.02129 -0.0910 0.1246 0.7659
10.000 1.3947 0.03073 0.02260 -0.0897 0.1175 0.7679
10.250 1.3999 0.03235 0.02429 -0.0882 0.0998 0.7698
10.500 1.3977 0.03469 0.02660 -0.0866 0.0940 0.7714
10.750 1.3963 0.03716 0.02907 -0.0853 0.0898 0.7731
11.000 1.3993 0.03934 0.03138 -0.0845 0.0852 0.7745
11.750 1.4022 0.04700 0.03921 -0.0826 0.0612 0.7791
12.000 1.3984 0.05027 0.04250 -0.0823 0.0580 0.7807
12.250 1.3974 0.05335 0.04569 -0.0821 0.0555 0.7824
12.500 1.3946 0.05674 0.04920 -0.0821 0.0535 0.7841
12.750 1.3898 0.06047 0.05303 -0.0822 0.0518 0.7860
13.000 1.3911 0.06356 0.05625 -0.0825 0.0502 0.7881
13.250 1.3975 0.06610 0.05896 -0.0828 0.0481 0.7903
13.500 1.4013 0.06897 0.06199 -0.0831 0.0460 0.7922
13.750 1.4029 0.07215 0.06531 -0.0835 0.0441 0.7939
14.000 1.4098 0.07467 0.06799 -0.0839 0.0418 0.7959
14.250 1.4162 0.07732 0.07081 -0.0844 0.0386 0.7980
14.500 1.4202 0.08033 0.07394 -0.0850 0.0359 0.8001
14.750 1.4233 0.08354 0.07720 -0.0857 0.0338 0.8024
15.000 1.4253 0.08695 0.08066 -0.0866 0.0319 0.8047
15.250 1.4262 0.09059 0.08435 -0.0876 0.0303 0.8070
15.500 1.4275 0.09418 0.08807 -0.0886 0.0290 0.8091
15.750 1.4285 0.09778 0.09180 -0.0896 0.0276 0.8113
16.000 1.4285 0.10162 0.09576 -0.0908 0.0260 0.8137
16.250 1.4273 0.10569 0.09992 -0.0921 0.0247 0.8162
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