S1046 17% (Danny Howell) (s1046-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1046 17% (Danny Howell) (s1046-il) Reynolds number: 500,000 Max Cl/Cd: 76.98 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1046-il-500000.txt Download as CSV file: xf-s1046-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S1046 17% (Danny Howell)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -1.0741 0.09553 0.09092 -0.0148 1.0000 0.0190
-17.750 -1.0859 0.09014 0.08547 -0.0172 1.0000 0.0195
-17.500 -1.0958 0.08511 0.08037 -0.0194 1.0000 0.0200
-17.250 -1.1045 0.08035 0.07553 -0.0214 1.0000 0.0206
-17.000 -1.1124 0.07582 0.07090 -0.0232 1.0000 0.0212
-16.750 -1.1192 0.07150 0.06649 -0.0249 1.0000 0.0220
-16.500 -1.1240 0.06755 0.06244 -0.0263 1.0000 0.0224
-16.250 -1.1378 0.06254 0.05735 -0.0282 1.0000 0.0231
-16.000 -1.1487 0.05801 0.05275 -0.0297 1.0000 0.0241
-15.750 -1.1557 0.05413 0.04879 -0.0309 1.0000 0.0250
-15.500 -1.1612 0.05054 0.04512 -0.0318 1.0000 0.0262
-15.250 -1.1655 0.04720 0.04169 -0.0326 1.0000 0.0275
-15.000 -1.1742 0.04356 0.03801 -0.0332 1.0000 0.0293
-14.750 -1.1785 0.04049 0.03487 -0.0336 1.0000 0.0310
-14.500 -1.1807 0.03775 0.03206 -0.0337 1.0000 0.0336
-14.250 -1.1852 0.03487 0.02916 -0.0337 1.0000 0.0364
-14.000 -1.1846 0.03259 0.02682 -0.0335 1.0000 0.0400
-13.750 -1.1874 0.03011 0.02433 -0.0330 1.0000 0.0442
-13.500 -1.1862 0.02809 0.02228 -0.0324 1.0000 0.0491
-13.250 -1.1845 0.02621 0.02039 -0.0315 1.0000 0.0545
-13.000 -1.1818 0.02451 0.01869 -0.0304 1.0000 0.0599
-12.750 -1.1757 0.02317 0.01731 -0.0292 1.0000 0.0657
-12.500 -1.1725 0.02174 0.01590 -0.0277 1.0000 0.0723
-12.250 -1.1655 0.02064 0.01480 -0.0261 1.0000 0.0789
-12.000 -1.1592 0.01961 0.01378 -0.0241 1.0000 0.0861
-11.750 -1.1523 0.01871 0.01288 -0.0220 1.0000 0.0935
-11.500 -1.1434 0.01797 0.01215 -0.0198 1.0000 0.1017
-11.250 -1.1362 0.01725 0.01146 -0.0171 1.0000 0.1102
-11.000 -1.1283 0.01663 0.01087 -0.0142 1.0000 0.1190
-10.750 -1.1174 0.01611 0.01037 -0.0117 1.0000 0.1286
-10.500 -1.1042 0.01557 0.00987 -0.0096 1.0000 0.1390
-10.250 -1.0903 0.01505 0.00938 -0.0076 1.0000 0.1495
-10.000 -1.0748 0.01460 0.00896 -0.0057 1.0000 0.1595
-9.500 -1.0430 0.01380 0.00822 -0.0020 1.0000 0.1794
-9.250 -1.0271 0.01344 0.00789 0.0000 1.0000 0.1891
-9.000 -1.0114 0.01315 0.00761 0.0020 1.0000 0.1997
-8.500 -0.9434 0.01239 0.00694 -0.0015 0.9868 0.2274
-8.250 -0.9054 0.01201 0.00660 -0.0039 0.9754 0.2396
-8.000 -0.8669 0.01167 0.00626 -0.0064 0.9608 0.2502
-7.750 -0.8285 0.01140 0.00596 -0.0087 0.9431 0.2609
-7.500 -0.7967 0.01115 0.00568 -0.0096 0.9202 0.2716
-7.250 -0.7722 0.01097 0.00544 -0.0089 0.8952 0.2808
-7.000 -0.7478 0.01088 0.00524 -0.0081 0.8743 0.2897
-6.750 -0.7247 0.01069 0.00502 -0.0071 0.8560 0.2984
-6.500 -0.6997 0.01059 0.00483 -0.0065 0.8398 0.3068
-6.250 -0.6752 0.01043 0.00464 -0.0058 0.8250 0.3157
-6.000 -0.6496 0.01031 0.00446 -0.0054 0.8112 0.3239
-5.750 -0.6241 0.01018 0.00430 -0.0049 0.7986 0.3329
-5.500 -0.5983 0.01006 0.00413 -0.0045 0.7869 0.3414
-5.250 -0.5721 0.00996 0.00398 -0.0041 0.7757 0.3508
-5.000 -0.5460 0.00982 0.00383 -0.0037 0.7644 0.3595
-4.500 -0.4930 0.00962 0.00357 -0.0031 0.7440 0.3779
-4.250 -0.4659 0.00952 0.00344 -0.0029 0.7338 0.3870
-4.000 -0.4393 0.00944 0.00333 -0.0026 0.7242 0.3967
-3.750 -0.4122 0.00933 0.00322 -0.0024 0.7140 0.4058
-3.500 -0.3849 0.00927 0.00312 -0.0022 0.7044 0.4157
-3.250 -0.3581 0.00917 0.00302 -0.0019 0.6945 0.4253
-3.000 -0.3306 0.00910 0.00294 -0.0018 0.6845 0.4351
-2.750 -0.3034 0.00904 0.00285 -0.0016 0.6752 0.4453
-2.500 -0.2760 0.00895 0.00278 -0.0014 0.6648 0.4553
-2.250 -0.2484 0.00891 0.00271 -0.0013 0.6551 0.4656
-2.000 -0.2211 0.00884 0.00264 -0.0011 0.6449 0.4759
-1.750 -0.1934 0.00878 0.00259 -0.0010 0.6345 0.4859
-1.500 -0.1657 0.00877 0.00254 -0.0008 0.6246 0.4967
-1.250 -0.1383 0.00870 0.00250 -0.0007 0.6138 0.5070
-1.000 -0.1106 0.00866 0.00246 -0.0005 0.6033 0.5174
-0.750 -0.0829 0.00866 0.00242 -0.0004 0.5930 0.5284
-0.500 -0.0554 0.00861 0.00241 -0.0003 0.5818 0.5388
-0.250 -0.0276 0.00860 0.00240 -0.0001 0.5711 0.5494
0.000 0.0000 0.00862 0.00238 0.0000 0.5607 0.5606
0.250 0.0276 0.00860 0.00240 0.0001 0.5494 0.5712
0.500 0.0554 0.00861 0.00241 0.0003 0.5388 0.5818
0.750 0.0829 0.00866 0.00242 0.0004 0.5284 0.5930
1.000 0.1106 0.00866 0.00246 0.0005 0.5174 0.6033
1.250 0.1383 0.00870 0.00250 0.0007 0.5070 0.6138
1.750 0.1935 0.00878 0.00259 0.0010 0.4859 0.6345
2.000 0.2211 0.00884 0.00265 0.0011 0.4759 0.6448
2.250 0.2484 0.00891 0.00271 0.0013 0.4656 0.6550
2.500 0.2760 0.00895 0.00278 0.0014 0.4552 0.6648
2.750 0.3034 0.00904 0.00285 0.0016 0.4453 0.6751
3.000 0.3306 0.00910 0.00294 0.0018 0.4351 0.6846
3.250 0.3581 0.00917 0.00302 0.0019 0.4254 0.6945
3.500 0.3849 0.00927 0.00312 0.0022 0.4157 0.7044
3.750 0.4122 0.00933 0.00322 0.0024 0.4058 0.7140
4.000 0.4393 0.00944 0.00333 0.0026 0.3967 0.7242
4.250 0.4659 0.00952 0.00344 0.0029 0.3869 0.7338
4.500 0.4930 0.00962 0.00357 0.0031 0.3778 0.7439
5.000 0.5460 0.00982 0.00383 0.0037 0.3595 0.7645
5.250 0.5721 0.00996 0.00398 0.0041 0.3507 0.7757
5.500 0.5983 0.01006 0.00413 0.0044 0.3415 0.7869
5.750 0.6241 0.01018 0.00429 0.0049 0.3328 0.7986
6.000 0.6496 0.01031 0.00446 0.0054 0.3239 0.8112
6.250 0.6752 0.01043 0.00464 0.0058 0.3155 0.8250
6.500 0.6997 0.01059 0.00483 0.0065 0.3068 0.8398
6.750 0.7247 0.01069 0.00502 0.0071 0.2983 0.8561
7.000 0.7478 0.01087 0.00524 0.0081 0.2897 0.8743
7.250 0.7723 0.01097 0.00544 0.0088 0.2808 0.8952
7.500 0.7967 0.01115 0.00568 0.0096 0.2716 0.9201
7.750 0.8286 0.01140 0.00596 0.0087 0.2610 0.9431
8.000 0.8670 0.01167 0.00626 0.0064 0.2503 0.9609
8.250 0.9055 0.01201 0.00660 0.0039 0.2397 0.9755
8.500 0.9435 0.01239 0.00694 0.0015 0.2273 0.9869
9.000 1.0115 0.01314 0.00761 -0.0020 0.2000 1.0000
9.250 1.0271 0.01344 0.00789 0.0000 0.1893 1.0000
9.500 1.0430 0.01380 0.00822 0.0020 0.1794 1.0000
10.000 1.0747 0.01460 0.00896 0.0057 0.1592 1.0000
10.250 1.0904 0.01505 0.00938 0.0076 0.1494 1.0000
10.500 1.1044 0.01557 0.00987 0.0096 0.1392 1.0000
10.750 1.1177 0.01611 0.01037 0.0117 0.1287 1.0000
11.000 1.1285 0.01664 0.01087 0.0142 0.1187 1.0000
11.250 1.1366 0.01724 0.01145 0.0170 0.1103 1.0000
11.500 1.1437 0.01797 0.01214 0.0197 0.1016 1.0000
11.750 1.1528 0.01870 0.01287 0.0219 0.0936 1.0000
12.000 1.1598 0.01961 0.01377 0.0241 0.0863 1.0000
12.250 1.1662 0.02063 0.01478 0.0260 0.0789 1.0000
12.500 1.1731 0.02173 0.01590 0.0276 0.0722 1.0000
12.750 1.1765 0.02315 0.01729 0.0292 0.0657 1.0000
13.000 1.1825 0.02451 0.01868 0.0303 0.0597 1.0000
13.250 1.1854 0.02619 0.02037 0.0314 0.0542 1.0000
13.500 1.1872 0.02806 0.02225 0.0322 0.0491 1.0000
13.750 1.1886 0.03007 0.02429 0.0329 0.0442 1.0000
14.000 1.1855 0.03258 0.02680 0.0333 0.0398 1.0000
14.250 1.1865 0.03484 0.02913 0.0336 0.0364 1.0000
14.500 1.1817 0.03773 0.03205 0.0336 0.0335 1.0000
14.750 1.1796 0.04048 0.03487 0.0334 0.0314 1.0000
15.000 1.1756 0.04352 0.03795 0.0331 0.0289 1.0000
15.250 1.1662 0.04724 0.04173 0.0324 0.0275 1.0000
15.500 1.1622 0.05055 0.04513 0.0316 0.0263 1.0000
15.750 1.1574 0.05406 0.04873 0.0307 0.0249 1.0000
16.000 1.1503 0.05798 0.05271 0.0295 0.0240 1.0000
16.250 1.1394 0.06250 0.05730 0.0279 0.0231 1.0000
16.500 1.1278 0.06724 0.06213 0.0262 0.0223 1.0000
16.750 1.1214 0.07140 0.06639 0.0247 0.0218 1.0000
17.000 1.1147 0.07570 0.07078 0.0230 0.0210 1.0000
17.250 1.1063 0.08030 0.07547 0.0211 0.0204 1.0000
17.500 1.0971 0.08516 0.08040 0.0191 0.0198 1.0000
17.750 1.0868 0.09024 0.08556 0.0169 0.0193 1.0000
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Polar data table (+)
Polar graphs
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