FX 63-158 AIRFOIL (fx63158-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-158 AIRFOIL (fx63158-il) Reynolds number: 500,000 Max Cl/Cd: 70.4 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63158-il-500000-n5.txt Download as CSV file: xf-fx63158-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0600 0.07872 0.07515 -0.1064 0.6989 0.0133
-10.500 -0.1044 0.05342 0.05003 -0.1176 0.7385 0.0088
-10.250 -0.1171 0.04810 0.04461 -0.1208 0.7209 0.0087
-10.000 -0.1363 0.04171 0.03818 -0.1248 0.7298 0.0086
-9.750 -0.1552 0.03746 0.03370 -0.1263 0.6989 0.0086
-9.500 -0.1716 0.03385 0.02996 -0.1271 0.6887 0.0085
-9.250 -0.1850 0.03099 0.02697 -0.1270 0.6811 0.0084
-9.000 -0.2000 0.02835 0.02420 -0.1260 0.6740 0.0083
-8.750 -0.2149 0.02642 0.02210 -0.1237 0.6607 0.0082
-8.250 -0.2518 0.03032 0.02501 -0.1248 0.6606 0.0065
-8.000 -0.2433 0.02828 0.02269 -0.1236 0.6408 0.0064
-7.750 -0.2308 0.02624 0.02036 -0.1226 0.6269 0.0064
-7.500 -0.2163 0.02417 0.01794 -0.1214 0.6104 0.0063
-7.250 -0.1987 0.02240 0.01586 -0.1204 0.5966 0.0062
-7.000 -0.1786 0.02085 0.01404 -0.1196 0.5816 0.0062
-6.750 -0.1573 0.01945 0.01241 -0.1187 0.5699 0.0062
-6.500 -0.1355 0.01830 0.01105 -0.1178 0.5593 0.0062
-6.250 -0.1132 0.01734 0.00991 -0.1170 0.5507 0.0062
-6.000 -0.0904 0.01655 0.00898 -0.1163 0.5435 0.0063
-5.750 -0.0665 0.01585 0.00818 -0.1159 0.5374 0.0064
-5.500 -0.0421 0.01526 0.00749 -0.1156 0.5316 0.0065
-5.250 -0.0173 0.01447 0.00662 -0.1157 0.5265 0.0068
-5.000 0.0098 0.01394 0.00604 -0.1161 0.5210 0.0071
-4.750 0.0374 0.01356 0.00560 -0.1165 0.5137 0.0074
-4.500 0.0656 0.01321 0.00519 -0.1170 0.5060 0.0078
-4.250 0.0935 0.01294 0.00481 -0.1175 0.4920 0.0081
-4.000 0.1213 0.01274 0.00447 -0.1178 0.4763 0.0085
-3.750 0.1494 0.01259 0.00421 -0.1183 0.4581 0.0093
-3.500 0.1771 0.01253 0.00404 -0.1186 0.4290 0.0102
-3.250 0.2049 0.01249 0.00384 -0.1189 0.4087 0.0108
-3.000 0.2335 0.01242 0.00365 -0.1193 0.3907 0.0115
-2.750 0.2605 0.01253 0.00356 -0.1195 0.3513 0.0129
-2.500 0.2885 0.01258 0.00346 -0.1198 0.3289 0.0156
-2.250 0.3150 0.01277 0.00343 -0.1198 0.2875 0.0192
-2.000 0.3416 0.01297 0.00348 -0.1200 0.2382 0.0243
-1.750 0.3690 0.01310 0.00349 -0.1201 0.2271 0.0346
-1.500 0.3971 0.01317 0.00348 -0.1204 0.2059 0.0393
-1.250 0.4240 0.01335 0.00353 -0.1205 0.1794 0.0424
-1.000 0.4523 0.01342 0.00354 -0.1208 0.1718 0.0453
-0.750 0.4831 0.01330 0.00352 -0.1218 0.1660 0.1040
-0.500 0.5117 0.01338 0.00360 -0.1224 0.1370 0.1361
-0.250 0.5397 0.01347 0.00365 -0.1226 0.1335 0.1461
0.000 0.5687 0.01350 0.00370 -0.1232 0.1304 0.1626
0.250 0.6002 0.01339 0.00373 -0.1245 0.1278 0.2406
0.500 0.6357 0.01308 0.00373 -0.1269 0.1260 0.3675
0.750 0.6716 0.01279 0.00375 -0.1293 0.1246 0.4794
1.000 0.7033 0.01273 0.00391 -0.1305 0.1231 0.5565
1.250 0.7314 0.01285 0.00411 -0.1307 0.1212 0.5868
1.500 0.7587 0.01301 0.00429 -0.1308 0.1194 0.6043
1.750 0.7857 0.01318 0.00446 -0.1308 0.1170 0.6162
2.000 0.8127 0.01335 0.00462 -0.1307 0.1153 0.6233
2.250 0.8397 0.01351 0.00477 -0.1307 0.1128 0.6301
2.500 0.8654 0.01379 0.00499 -0.1305 0.0964 0.6367
2.750 0.8912 0.01401 0.00523 -0.1302 0.0954 0.6441
3.000 0.9171 0.01425 0.00545 -0.1300 0.0943 0.6528
3.250 0.9424 0.01449 0.00570 -0.1297 0.0931 0.6590
3.500 0.9678 0.01472 0.00594 -0.1294 0.0919 0.6642
3.750 0.9932 0.01496 0.00617 -0.1291 0.0902 0.6673
4.000 1.0186 0.01520 0.00640 -0.1289 0.0884 0.6705
4.250 1.0435 0.01542 0.00665 -0.1285 0.0871 0.6731
4.500 1.0679 0.01566 0.00693 -0.1281 0.0857 0.6755
4.750 1.0922 0.01591 0.00720 -0.1276 0.0846 0.6777
5.000 1.1163 0.01617 0.00748 -0.1272 0.0836 0.6801
5.250 1.1400 0.01644 0.00778 -0.1266 0.0826 0.6825
5.500 1.1633 0.01673 0.00809 -0.1261 0.0816 0.6849
5.750 1.1862 0.01704 0.00842 -0.1254 0.0806 0.6871
6.000 1.2088 0.01732 0.00874 -0.1247 0.0798 0.6892
6.250 1.2313 0.01757 0.00905 -0.1240 0.0791 0.6913
6.500 1.2529 0.01783 0.00937 -0.1231 0.0782 0.6934
6.750 1.2735 0.01809 0.00968 -0.1220 0.0761 0.6956
7.000 1.2914 0.01847 0.01009 -0.1205 0.0639 0.6978
7.250 1.3065 0.01901 0.01059 -0.1186 0.0617 0.6999
7.500 1.3224 0.01953 0.01110 -0.1168 0.0590 0.7019
7.750 1.3391 0.02001 0.01163 -0.1153 0.0576 0.7037
8.000 1.3550 0.02053 0.01220 -0.1136 0.0568 0.7053
8.250 1.3689 0.02114 0.01289 -0.1117 0.0555 0.7067
8.500 1.3800 0.02191 0.01373 -0.1095 0.0539 0.7078
8.750 1.3888 0.02283 0.01472 -0.1071 0.0519 0.7089
9.000 1.4010 0.02359 0.01555 -0.1053 0.0505 0.7101
9.250 1.4156 0.02425 0.01629 -0.1039 0.0491 0.7115
9.500 1.4286 0.02502 0.01716 -0.1023 0.0471 0.7130
9.750 1.4400 0.02594 0.01815 -0.1007 0.0450 0.7147
10.000 1.4510 0.02693 0.01921 -0.0992 0.0434 0.7163
10.250 1.4642 0.02782 0.02018 -0.0981 0.0410 0.7176
10.500 1.4741 0.02900 0.02140 -0.0967 0.0347 0.7189
10.750 1.4787 0.03065 0.02302 -0.0951 0.0305 0.7201
11.000 1.4843 0.03234 0.02476 -0.0939 0.0281 0.7212
11.250 1.4882 0.03428 0.02675 -0.0927 0.0260 0.7223
11.500 1.4914 0.03638 0.02892 -0.0916 0.0241 0.7235
11.750 1.4975 0.03832 0.03095 -0.0909 0.0228 0.7247
12.000 1.5025 0.04043 0.03316 -0.0903 0.0205 0.7259
12.250 1.5045 0.04294 0.03573 -0.0897 0.0177 0.7271
12.500 1.5059 0.04558 0.03842 -0.0892 0.0155 0.7284
12.750 1.5060 0.04844 0.04133 -0.0889 0.0134 0.7297
13.000 1.5075 0.05122 0.04419 -0.0887 0.0120 0.7311
13.250 1.5078 0.05421 0.04724 -0.0885 0.0106 0.7326
13.500 1.5095 0.05711 0.05022 -0.0885 0.0095 0.7342
14.000 1.5035 0.06434 0.05756 -0.0889 0.0033 0.7369
14.250 1.5016 0.06796 0.06127 -0.0892 0.0029 0.7381
14.500 1.5010 0.07151 0.06491 -0.0897 0.0027 0.7393
14.750 1.5012 0.07499 0.06850 -0.0902 0.0025 0.7404
15.000 1.5016 0.07854 0.07216 -0.0909 0.0024 0.7417
15.250 1.5023 0.08213 0.07586 -0.0916 0.0023 0.7429
15.500 1.5025 0.08583 0.07969 -0.0925 0.0022 0.7443
15.750 1.5023 0.08965 0.08363 -0.0934 0.0022 0.7456
16.000 1.5022 0.09350 0.08758 -0.0945 0.0021 0.7471
16.250 1.5014 0.09752 0.09173 -0.0956 0.0021 0.7485
16.500 1.5005 0.10162 0.09594 -0.0969 0.0020 0.7500
16.750 1.4991 0.10583 0.10028 -0.0983 0.0020 0.7515
17.000 1.4977 0.11009 0.10465 -0.0998 0.0019 0.7530
17.250 1.4960 0.11442 0.10911 -0.1014 0.0019 0.7545
17.500 1.4936 0.11892 0.11372 -0.1031 0.0018 0.7559
17.750 1.4911 0.12345 0.11838 -0.1050 0.0018 0.7573
18.000 1.4884 0.12807 0.12313 -0.1070 0.0017 0.7589
18.250 1.4845 0.13294 0.12814 -0.1093 0.0017 0.7605
18.500 1.4799 0.13799 0.13331 -0.1118 0.0016 0.7621
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