FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-145 AIRFOIL (fx63145-il) Reynolds number: 200,000 Max Cl/Cd: 75.57 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63145-il-200000.txt Download as CSV file: xf-fx63145-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-145 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2853 0.09693 0.09387 -0.0420 1.0000 0.0442
-9.000 -0.3055 0.09089 0.08794 -0.0476 1.0000 0.0452
-8.750 -0.3249 0.08446 0.08159 -0.0529 0.9997 0.0453
-8.500 -0.2842 0.08431 0.08144 -0.0489 0.9953 0.0471
-8.250 -0.2683 0.08009 0.07724 -0.0531 0.9791 0.0490
-8.000 -0.2670 0.07218 0.06935 -0.0631 0.9476 0.0515
-7.500 -0.2237 0.05364 0.05041 -0.0978 0.8816 0.0568
-7.250 -0.1964 0.04614 0.04228 -0.1127 0.8403 0.0629
-6.750 -0.1504 0.03949 0.03488 -0.1198 0.7727 0.0730
-6.500 -0.1349 0.03689 0.03177 -0.1213 0.7477 0.0806
-6.250 -0.1153 0.03501 0.02959 -0.1219 0.7283 0.0897
-6.000 -0.0949 0.03307 0.02744 -0.1223 0.7103 0.0996
-5.750 -0.0736 0.03093 0.02513 -0.1227 0.6943 0.1102
-5.500 -0.0317 0.02492 0.01751 -0.1201 0.6842 0.0375
-5.250 -0.0049 0.02245 0.01469 -0.1192 0.6718 0.0306
-5.000 0.0214 0.02065 0.01256 -0.1184 0.6596 0.0277
-4.750 0.0481 0.01964 0.01126 -0.1176 0.6478 0.0262
-4.500 0.0731 0.01850 0.01005 -0.1168 0.6347 0.0256
-4.250 0.0985 0.01753 0.00903 -0.1161 0.6233 0.0251
-4.000 0.1246 0.01672 0.00814 -0.1157 0.6132 0.0248
-3.750 0.1522 0.01596 0.00733 -0.1159 0.6037 0.0249
-3.500 0.1811 0.01533 0.00659 -0.1163 0.5951 0.0254
-3.250 0.2108 0.01484 0.00596 -0.1168 0.5860 0.0265
-3.000 0.2402 0.01451 0.00552 -0.1172 0.5777 0.0292
-2.750 0.2701 0.01420 0.00508 -0.1176 0.5695 0.0366
-2.500 0.3026 0.01337 0.00446 -0.1190 0.5624 0.1405
-2.250 0.3371 0.01212 0.00424 -0.1218 0.5553 0.4239
-2.000 0.3659 0.01207 0.00428 -0.1219 0.5492 0.4899
-1.750 0.3943 0.01212 0.00437 -0.1219 0.5433 0.5284
-1.500 0.4229 0.01225 0.00446 -0.1219 0.5374 0.5642
-1.250 0.4510 0.01238 0.00450 -0.1217 0.5325 0.5832
-1.000 0.4790 0.01251 0.00462 -0.1216 0.5277 0.6011
-0.750 0.5064 0.01269 0.00482 -0.1212 0.5224 0.6233
-0.500 0.5349 0.01279 0.00482 -0.1212 0.5170 0.6341
-0.250 0.5624 0.01286 0.00488 -0.1210 0.5117 0.6410
0.000 0.5910 0.01293 0.00490 -0.1211 0.5058 0.6501
0.250 0.6179 0.01301 0.00497 -0.1208 0.5002 0.6573
0.500 0.6463 0.01311 0.00501 -0.1208 0.4942 0.6663
0.750 0.6730 0.01318 0.00507 -0.1205 0.4874 0.6732
1.000 0.7006 0.01329 0.00510 -0.1204 0.4807 0.6814
1.250 0.7279 0.01336 0.00517 -0.1203 0.4732 0.6877
1.500 0.7547 0.01347 0.00523 -0.1200 0.4664 0.6945
1.750 0.7825 0.01354 0.00534 -0.1200 0.4590 0.7027
2.000 0.8087 0.01365 0.00549 -0.1196 0.4515 0.7134
2.250 0.8348 0.01375 0.00565 -0.1191 0.4450 0.7244
2.500 0.8623 0.01386 0.00577 -0.1190 0.4378 0.7352
2.750 0.8882 0.01394 0.00589 -0.1186 0.4311 0.7418
3.000 0.9155 0.01405 0.00600 -0.1185 0.4248 0.7493
3.250 0.9412 0.01416 0.00611 -0.1181 0.4189 0.7558
3.500 0.9674 0.01428 0.00626 -0.1178 0.4130 0.7638
3.750 0.9930 0.01442 0.00641 -0.1174 0.4061 0.7720
4.000 1.0184 0.01457 0.00661 -0.1170 0.3982 0.7808
4.250 1.0438 0.01471 0.00681 -0.1166 0.3865 0.7896
4.500 1.0693 0.01485 0.00700 -0.1162 0.3713 0.7997
4.750 1.0921 0.01505 0.00719 -0.1153 0.3605 0.8095
5.000 1.1156 0.01526 0.00742 -0.1145 0.3527 0.8211
5.250 1.1380 0.01548 0.00766 -0.1135 0.3454 0.8332
5.500 1.1597 0.01568 0.00792 -0.1124 0.3389 0.8461
5.750 1.1825 0.01581 0.00819 -0.1114 0.3305 0.8602
6.000 1.2039 0.01596 0.00844 -0.1102 0.3198 0.8758
6.250 1.2220 0.01617 0.00869 -0.1084 0.3042 0.8944
6.500 1.2357 0.01642 0.00894 -0.1059 0.2933 0.9209
6.750 1.2537 0.01664 0.00918 -0.1043 0.2850 1.0000
7.000 1.2838 0.01709 0.00965 -0.1055 0.2771 1.0000
7.250 1.3121 0.01752 0.01013 -0.1062 0.2664 1.0000
7.500 1.3370 0.01805 0.01065 -0.1064 0.2449 1.0000
7.750 1.3528 0.01903 0.01141 -0.1051 0.2290 1.0000
8.500 1.4063 0.02125 0.01353 -0.1019 0.1835 1.0000
8.750 1.4157 0.02222 0.01443 -0.0995 0.1766 1.0000
9.000 1.4289 0.02301 0.01528 -0.0977 0.1698 1.0000
9.250 1.4389 0.02395 0.01626 -0.0956 0.1657 1.0000
9.500 1.4608 0.02429 0.01678 -0.0949 0.1553 1.0000
9.750 1.4682 0.02540 0.01783 -0.0927 0.1420 1.0000
10.000 1.4695 0.02692 0.01923 -0.0901 0.1362 1.0000
10.250 1.4714 0.02850 0.02084 -0.0878 0.1313 1.0000
10.500 1.4717 0.03034 0.02273 -0.0857 0.1275 1.0000
10.750 1.4694 0.03256 0.02498 -0.0839 0.1248 1.0000
11.000 1.4831 0.03366 0.02626 -0.0833 0.1185 1.0000
11.250 1.5045 0.03415 0.02696 -0.0830 0.1055 1.0000
11.500 1.5051 0.03646 0.02922 -0.0821 0.1000 1.0000
11.750 1.5046 0.03903 0.03175 -0.0814 0.0961 1.0000
12.000 1.5014 0.04202 0.03475 -0.0809 0.0935 1.0000
12.250 1.4974 0.04524 0.03802 -0.0806 0.0914 1.0000
12.500 1.4961 0.04828 0.04116 -0.0804 0.0894 1.0000
12.750 1.4974 0.05110 0.04413 -0.0804 0.0873 1.0000
13.000 1.4955 0.05435 0.04750 -0.0805 0.0851 1.0000
13.250 1.4907 0.05801 0.05126 -0.0807 0.0833 1.0000
13.500 1.4925 0.06095 0.05434 -0.0809 0.0812 1.0000
13.750 1.5168 0.06116 0.05489 -0.0807 0.0736 1.0000
14.000 1.5126 0.06496 0.05864 -0.0813 0.0587 1.0000
14.250 1.5035 0.06952 0.06314 -0.0822 0.0551 1.0000
14.500 1.5004 0.07341 0.06716 -0.0829 0.0527 1.0000
14.750 1.4966 0.07751 0.07142 -0.0838 0.0503 1.0000
15.000 1.4895 0.08220 0.07625 -0.0850 0.0480 1.0000
15.250 1.4823 0.08704 0.08121 -0.0863 0.0459 1.0000
15.500 1.4930 0.08917 0.08360 -0.0868 0.0369 1.0000
15.750 1.4840 0.09441 0.08888 -0.0885 0.0300 1.0000
16.000 1.4751 0.09982 0.09432 -0.0903 0.0251 1.0000
16.250 1.4643 0.10566 0.10021 -0.0926 0.0213 1.0000
16.500 1.4557 0.11128 0.10595 -0.0948 0.0183 1.0000
16.750 1.4448 0.11743 0.11221 -0.0975 0.0160 1.0000
17.000 1.4324 0.12399 0.11889 -0.1005 0.0146 1.0000
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