S1048 14% (Danny Howell) (s1048-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S1048 14% (Danny Howell) (s1048-il) Reynolds number: 50,000 Max Cl/Cd: 24.17 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1048-il-50000.txt Download as CSV file: xf-s1048-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S1048 14% (Danny Howell)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6520 0.13404 0.12683 0.0053 1.0000 0.1594
-12.750 -0.6545 0.12779 0.12061 0.0030 1.0000 0.1589
-12.500 -0.6626 0.12085 0.11373 0.0001 1.0000 0.1587
-12.250 -0.8165 0.08369 0.07687 -0.0267 1.0000 0.1175
-12.000 -0.8454 0.07622 0.06933 -0.0304 1.0000 0.1161
-11.750 -0.8752 0.06978 0.06276 -0.0329 1.0000 0.1144
-11.500 -0.9048 0.06441 0.05721 -0.0338 1.0000 0.1132
-11.250 -0.9301 0.06016 0.05273 -0.0328 1.0000 0.1133
-11.000 -0.9497 0.05651 0.04881 -0.0305 1.0000 0.1144
-10.750 -0.9654 0.05288 0.04477 -0.0282 1.0000 0.1167
-10.500 -0.9551 0.05010 0.04203 -0.0270 1.0000 0.1248
-10.250 -0.9612 0.04684 0.03831 -0.0244 1.0000 0.1309
-10.000 -0.9496 0.04424 0.03574 -0.0229 1.0000 0.1433
-9.750 -0.9434 0.04181 0.03317 -0.0207 1.0000 0.1584
-9.500 -0.9297 0.04003 0.03169 -0.0188 1.0000 0.1805
-9.250 -0.9225 0.03838 0.03010 -0.0163 1.0000 0.2055
-9.000 -0.9102 0.03765 0.02962 -0.0137 1.0000 0.2362
-8.750 -0.8949 0.03748 0.02965 -0.0110 1.0000 0.2687
-8.500 -0.8772 0.03748 0.02976 -0.0084 1.0000 0.3000
-8.250 -0.8548 0.03776 0.03011 -0.0061 1.0000 0.3292
-8.000 -0.8297 0.03819 0.03059 -0.0038 1.0000 0.3560
-7.750 -0.8173 0.03735 0.02961 -0.0014 1.0000 0.3794
-7.500 -0.7819 0.03857 0.03090 0.0006 1.0000 0.4031
-7.250 -0.7739 0.03715 0.02930 0.0030 1.0000 0.4236
-7.000 -0.7384 0.03815 0.03032 0.0049 1.0000 0.4432
-6.750 -0.7147 0.03811 0.03020 0.0070 1.0000 0.4620
-6.500 -0.6987 0.03732 0.02932 0.0091 1.0000 0.4801
-6.250 -0.6876 0.03619 0.02807 0.0113 1.0000 0.4982
-6.000 -0.6678 0.03576 0.02756 0.0134 1.0000 0.5149
-5.750 -0.6468 0.03546 0.02721 0.0156 1.0000 0.5309
-5.500 -0.6283 0.03499 0.02669 0.0178 1.0000 0.5467
-5.250 -0.6117 0.03442 0.02607 0.0200 1.0000 0.5622
-5.000 -0.5967 0.03379 0.02540 0.0224 1.0000 0.5775
-4.750 -0.5836 0.03312 0.02468 0.0248 1.0000 0.5926
-4.500 -0.5723 0.03246 0.02399 0.0275 1.0000 0.6076
-4.250 -0.5630 0.03178 0.02327 0.0302 1.0000 0.6224
-4.000 -0.5549 0.03112 0.02258 0.0331 1.0000 0.6372
-3.750 -0.5475 0.03049 0.02192 0.0360 1.0000 0.6520
-3.500 -0.5397 0.02993 0.02131 0.0387 1.0000 0.6670
-3.250 -0.5314 0.02940 0.02075 0.0413 1.0000 0.6821
-3.000 -0.5224 0.02894 0.02027 0.0438 1.0000 0.6975
-2.750 -0.5126 0.02854 0.01984 0.0462 1.0000 0.7131
-2.500 -0.5020 0.02821 0.01949 0.0485 1.0000 0.7291
-2.250 -0.4911 0.02790 0.01915 0.0506 1.0000 0.7454
-2.000 -0.4797 0.02764 0.01887 0.0526 1.0000 0.7624
-1.750 -0.4679 0.02739 0.01861 0.0544 1.0000 0.7801
-1.500 -0.4563 0.02714 0.01834 0.0561 1.0000 0.7992
-1.250 -0.4313 0.02718 0.01833 0.0553 0.9955 0.8198
-1.000 -0.3659 0.02806 0.01915 0.0481 0.9792 0.8408
-0.750 -0.3019 0.02872 0.01972 0.0408 0.9626 0.8631
-0.500 -0.2164 0.02958 0.02053 0.0300 0.9464 0.8819
-0.250 -0.1153 0.03030 0.02118 0.0163 0.9304 0.8989
0.000 0.0001 0.03058 0.02144 0.0000 0.9146 0.9146
0.250 0.1161 0.03029 0.02117 -0.0165 0.8989 0.9304
0.500 0.2163 0.02958 0.02052 -0.0299 0.8818 0.9463
0.750 0.3017 0.02872 0.01972 -0.0407 0.8631 0.9625
1.000 0.3659 0.02807 0.01916 -0.0481 0.8410 0.9792
1.250 0.4314 0.02718 0.01833 -0.0554 0.8199 0.9956
1.500 0.4562 0.02714 0.01834 -0.0561 0.7992 1.0000
1.750 0.4679 0.02739 0.01861 -0.0544 0.7802 1.0000
2.000 0.4796 0.02764 0.01887 -0.0526 0.7625 1.0000
2.250 0.4910 0.02791 0.01915 -0.0506 0.7455 1.0000
2.500 0.5021 0.02820 0.01948 -0.0484 0.7291 1.0000
2.750 0.5125 0.02854 0.01984 -0.0462 0.7131 1.0000
3.000 0.5224 0.02894 0.02026 -0.0438 0.6975 1.0000
3.250 0.5314 0.02940 0.02075 -0.0413 0.6821 1.0000
3.500 0.5396 0.02992 0.02130 -0.0387 0.6670 1.0000
3.750 0.5474 0.03049 0.02192 -0.0359 0.6520 1.0000
4.000 0.5549 0.03111 0.02258 -0.0331 0.6372 1.0000
4.250 0.5631 0.03176 0.02325 -0.0302 0.6223 1.0000
4.500 0.5724 0.03245 0.02397 -0.0274 0.6075 1.0000
4.750 0.5835 0.03313 0.02468 -0.0248 0.5926 1.0000
5.000 0.5968 0.03379 0.02540 -0.0224 0.5775 1.0000
5.250 0.6117 0.03441 0.02607 -0.0200 0.5622 1.0000
5.500 0.6283 0.03498 0.02668 -0.0178 0.5467 1.0000
5.750 0.6469 0.03544 0.02720 -0.0156 0.5309 1.0000
6.000 0.6680 0.03573 0.02753 -0.0134 0.5149 1.0000
6.250 0.6876 0.03618 0.02806 -0.0113 0.4982 1.0000
6.500 0.6988 0.03732 0.02931 -0.0091 0.4801 1.0000
6.750 0.7147 0.03810 0.03019 -0.0070 0.4620 1.0000
7.000 0.7382 0.03818 0.03034 -0.0049 0.4432 1.0000
7.250 0.7740 0.03715 0.02930 -0.0030 0.4236 1.0000
7.500 0.7819 0.03857 0.03091 -0.0006 0.4030 1.0000
7.750 0.8171 0.03738 0.02964 0.0014 0.3795 1.0000
8.000 0.8300 0.03816 0.03055 0.0038 0.3557 1.0000
8.250 0.8548 0.03776 0.03011 0.0061 0.3292 1.0000
8.500 0.8772 0.03748 0.02976 0.0084 0.2999 1.0000
8.750 0.8950 0.03748 0.02964 0.0110 0.2687 1.0000
9.000 0.9101 0.03766 0.02963 0.0137 0.2363 1.0000
9.250 0.9225 0.03838 0.03011 0.0163 0.2055 1.0000
9.500 0.9298 0.04005 0.03170 0.0188 0.1804 1.0000
9.750 0.9434 0.04181 0.03318 0.0207 0.1584 1.0000
10.000 0.9499 0.04426 0.03575 0.0229 0.1434 1.0000
10.250 0.9615 0.04684 0.03831 0.0244 0.1310 1.0000
10.500 0.9552 0.05009 0.04202 0.0269 0.1248 1.0000
10.750 0.9652 0.05288 0.04477 0.0282 0.1167 1.0000
11.000 0.9495 0.05651 0.04880 0.0305 0.1143 1.0000
11.250 0.9299 0.06018 0.05275 0.0327 0.1132 1.0000
11.500 0.9050 0.06445 0.05725 0.0337 0.1133 1.0000
11.750 0.8755 0.06979 0.06278 0.0328 0.1144 1.0000
12.000 0.8443 0.07639 0.06951 0.0302 0.1160 1.0000
12.250 0.8172 0.08371 0.07688 0.0266 0.1175 1.0000
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Polar data table (+)
Polar graphs
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