S1048 14% (Danny Howell) (s1048-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S1048 14% (Danny Howell) (s1048-il) Reynolds number: 500,000 Max Cl/Cd: 66.11 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1048-il-500000-n5.txt Download as CSV file: xf-s1048-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -1.0292 0.10081 0.09684 -0.0050 1.0000 0.0051
-17.000 -1.0396 0.09500 0.09093 -0.0079 1.0000 0.0051
-16.750 -1.0491 0.08949 0.08532 -0.0106 1.0000 0.0051
-16.500 -1.0590 0.08401 0.07973 -0.0133 1.0000 0.0052
-16.250 -1.0678 0.07885 0.07446 -0.0158 1.0000 0.0052
-16.000 -1.0756 0.07399 0.06949 -0.0180 1.0000 0.0052
-15.750 -1.0850 0.06902 0.06441 -0.0203 1.0000 0.0053
-15.500 -1.0930 0.06441 0.05968 -0.0223 1.0000 0.0053
-15.250 -1.1006 0.06000 0.05516 -0.0241 1.0000 0.0054
-15.000 -1.1060 0.05605 0.05110 -0.0256 1.0000 0.0054
-14.750 -1.1124 0.05209 0.04703 -0.0271 1.0000 0.0054
-14.500 -1.1201 0.04808 0.04291 -0.0284 1.0000 0.0055
-14.250 -1.1274 0.04426 0.03898 -0.0295 1.0000 0.0056
-14.000 -1.1327 0.04081 0.03542 -0.0304 1.0000 0.0057
-13.750 -1.1358 0.03776 0.03228 -0.0309 1.0000 0.0059
-13.500 -1.1360 0.03515 0.02956 -0.0311 1.0000 0.0059
-13.250 -1.1352 0.03277 0.02710 -0.0311 1.0000 0.0063
-13.000 -1.1320 0.03076 0.02500 -0.0308 1.0000 0.0063
-12.750 -1.1282 0.02892 0.02308 -0.0302 1.0000 0.0065
-12.500 -1.1237 0.02729 0.02135 -0.0294 1.0000 0.0068
-12.250 -1.1187 0.02583 0.01980 -0.0282 1.0000 0.0070
-12.000 -1.1121 0.02459 0.01848 -0.0268 1.0000 0.0073
-11.750 -1.1057 0.02346 0.01727 -0.0250 1.0000 0.0076
-11.500 -1.0978 0.02252 0.01625 -0.0231 1.0000 0.0078
-11.250 -1.0906 0.02162 0.01528 -0.0207 1.0000 0.0082
-11.000 -1.0837 0.02079 0.01440 -0.0180 1.0000 0.0089
-10.750 -1.0725 0.02011 0.01369 -0.0158 1.0000 0.0097
-10.500 -1.0578 0.01946 0.01298 -0.0141 1.0000 0.0105
-10.250 -1.0419 0.01884 0.01229 -0.0126 1.0000 0.0116
-10.000 -1.0264 0.01816 0.01157 -0.0110 1.0000 0.0129
-9.750 -1.0089 0.01758 0.01096 -0.0096 1.0000 0.0144
-9.500 -0.9909 0.01703 0.01036 -0.0082 1.0000 0.0161
-9.250 -0.9729 0.01646 0.00978 -0.0068 1.0000 0.0184
-9.000 -0.9538 0.01596 0.00925 -0.0055 1.0000 0.0209
-8.750 -0.9354 0.01542 0.00872 -0.0041 1.0000 0.0254
-8.500 -0.9173 0.01487 0.00819 -0.0027 1.0000 0.0322
-8.250 -0.8991 0.01433 0.00770 -0.0012 1.0000 0.0414
-8.000 -0.8808 0.01382 0.00724 0.0003 1.0000 0.0522
-7.750 -0.8558 0.01325 0.00674 0.0003 0.9964 0.0678
-7.500 -0.8242 0.01261 0.00622 -0.0011 0.9865 0.0899
-7.250 -0.7929 0.01199 0.00573 -0.0024 0.9722 0.1157
-7.000 -0.7580 0.01147 0.00530 -0.0043 0.9551 0.1391
-6.750 -0.7223 0.01106 0.00492 -0.0062 0.9341 0.1593
-6.500 -0.6923 0.01063 0.00456 -0.0069 0.9081 0.1856
-6.250 -0.6678 0.01029 0.00425 -0.0064 0.8813 0.2115
-6.000 -0.6437 0.01003 0.00399 -0.0057 0.8575 0.2326
-5.750 -0.6190 0.00986 0.00377 -0.0050 0.8362 0.2470
-5.500 -0.5940 0.00968 0.00356 -0.0045 0.8168 0.2631
-5.250 -0.5689 0.00950 0.00336 -0.0040 0.7988 0.2812
-5.000 -0.5432 0.00936 0.00317 -0.0035 0.7822 0.2963
-4.750 -0.5171 0.00923 0.00301 -0.0032 0.7664 0.3096
-4.500 -0.4908 0.00911 0.00286 -0.0028 0.7516 0.3225
-4.250 -0.4642 0.00901 0.00272 -0.0026 0.7374 0.3348
-4.000 -0.4376 0.00891 0.00258 -0.0023 0.7238 0.3476
-3.750 -0.4107 0.00883 0.00246 -0.0021 0.7107 0.3600
-3.500 -0.3839 0.00874 0.00234 -0.0019 0.6979 0.3718
-3.250 -0.3569 0.00866 0.00223 -0.0016 0.6854 0.3831
-3.000 -0.3297 0.00859 0.00214 -0.0015 0.6730 0.3942
-2.750 -0.3023 0.00853 0.00205 -0.0013 0.6608 0.4053
-2.500 -0.2750 0.00847 0.00197 -0.0012 0.6487 0.4164
-2.250 -0.2477 0.00841 0.00189 -0.0010 0.6367 0.4276
-2.000 -0.2203 0.00837 0.00183 -0.0009 0.6247 0.4385
-1.750 -0.1928 0.00833 0.00177 -0.0008 0.6123 0.4498
-1.500 -0.1653 0.00829 0.00172 -0.0007 0.6001 0.4610
-1.250 -0.1378 0.00825 0.00168 -0.0005 0.5880 0.4719
-1.000 -0.1102 0.00823 0.00164 -0.0004 0.5762 0.4830
-0.750 -0.0827 0.00822 0.00161 -0.0003 0.5640 0.4941
-0.250 -0.0276 0.00819 0.00158 -0.0001 0.5401 0.5170
0.000 0.0000 0.00819 0.00158 0.0000 0.5286 0.5285
0.250 0.0276 0.00819 0.00158 0.0001 0.5170 0.5401
0.750 0.0827 0.00822 0.00161 0.0003 0.4942 0.5641
1.000 0.1102 0.00823 0.00164 0.0004 0.4831 0.5761
1.250 0.1378 0.00825 0.00168 0.0005 0.4719 0.5880
1.500 0.1653 0.00829 0.00172 0.0007 0.4611 0.6002
1.750 0.1927 0.00833 0.00177 0.0008 0.4496 0.6123
2.000 0.2203 0.00837 0.00183 0.0009 0.4385 0.6246
2.250 0.2477 0.00841 0.00189 0.0010 0.4275 0.6365
2.500 0.2750 0.00847 0.00197 0.0012 0.4163 0.6487
2.750 0.3022 0.00853 0.00205 0.0013 0.4051 0.6606
3.000 0.3296 0.00859 0.00214 0.0015 0.3940 0.6730
3.250 0.3569 0.00866 0.00223 0.0016 0.3831 0.6854
3.500 0.3838 0.00874 0.00234 0.0019 0.3716 0.6979
3.750 0.4107 0.00883 0.00246 0.0021 0.3600 0.7108
4.000 0.4375 0.00891 0.00258 0.0023 0.3476 0.7239
4.250 0.4642 0.00901 0.00272 0.0026 0.3349 0.7374
4.500 0.4908 0.00912 0.00286 0.0028 0.3224 0.7516
4.750 0.5171 0.00923 0.00301 0.0032 0.3099 0.7665
5.000 0.5432 0.00936 0.00317 0.0035 0.2962 0.7821
5.250 0.5689 0.00950 0.00336 0.0040 0.2810 0.7988
5.500 0.5940 0.00968 0.00356 0.0045 0.2632 0.8169
6.000 0.6437 0.01004 0.00399 0.0057 0.2323 0.8573
6.250 0.6677 0.01028 0.00424 0.0064 0.2117 0.8813
6.500 0.6923 0.01063 0.00456 0.0069 0.1857 0.9081
6.750 0.7223 0.01106 0.00492 0.0062 0.1590 0.9342
7.000 0.7580 0.01147 0.00530 0.0043 0.1389 0.9551
7.250 0.7927 0.01199 0.00573 0.0024 0.1156 0.9721
7.500 0.8242 0.01260 0.00622 0.0011 0.0908 0.9864
7.750 0.8557 0.01324 0.00674 -0.0003 0.0682 0.9962
8.000 0.8808 0.01382 0.00724 -0.0003 0.0520 1.0000
8.250 0.8991 0.01433 0.00770 0.0012 0.0413 1.0000
8.500 0.9173 0.01487 0.00819 0.0027 0.0323 1.0000
8.750 0.9354 0.01542 0.00872 0.0042 0.0253 1.0000
9.000 0.9539 0.01595 0.00924 0.0055 0.0211 1.0000
9.250 0.9728 0.01646 0.00977 0.0068 0.0184 1.0000
9.500 0.9909 0.01702 0.01035 0.0082 0.0162 1.0000
9.750 1.0089 0.01758 0.01096 0.0096 0.0145 1.0000
10.000 1.0264 0.01816 0.01157 0.0110 0.0129 1.0000
10.250 1.0421 0.01883 0.01227 0.0125 0.0117 1.0000
10.500 1.0578 0.01946 0.01297 0.0141 0.0105 1.0000
10.750 1.0726 0.02010 0.01367 0.0158 0.0096 1.0000
11.000 1.0836 0.02079 0.01441 0.0180 0.0090 1.0000
11.250 1.0908 0.02161 0.01527 0.0207 0.0082 1.0000
11.500 1.0979 0.02252 0.01624 0.0231 0.0079 1.0000
11.750 1.1057 0.02346 0.01727 0.0250 0.0075 1.0000
12.000 1.1126 0.02456 0.01845 0.0267 0.0074 1.0000
12.250 1.1186 0.02583 0.01980 0.0282 0.0070 1.0000
12.500 1.1246 0.02723 0.02128 0.0293 0.0067 1.0000
12.750 1.1288 0.02889 0.02305 0.0302 0.0066 1.0000
13.000 1.1325 0.03073 0.02497 0.0308 0.0062 1.0000
13.250 1.1352 0.03280 0.02713 0.0310 0.0062 1.0000
13.500 1.1364 0.03514 0.02955 0.0311 0.0060 1.0000
13.750 1.1353 0.03784 0.03236 0.0308 0.0059 1.0000
14.000 1.1336 0.04075 0.03537 0.0303 0.0058 1.0000
14.250 1.1267 0.04439 0.03911 0.0294 0.0056 1.0000
14.500 1.1215 0.04796 0.04280 0.0284 0.0055 1.0000
14.750 1.1122 0.05219 0.04713 0.0269 0.0054 1.0000
15.000 1.1093 0.05570 0.05075 0.0256 0.0054 1.0000
15.250 1.1027 0.05979 0.05494 0.0241 0.0053 1.0000
15.500 1.0949 0.06424 0.05951 0.0222 0.0053 1.0000
15.750 1.0855 0.06906 0.06444 0.0201 0.0053 1.0000
16.000 1.0781 0.07375 0.06925 0.0180 0.0052 1.0000
16.250 1.0705 0.07858 0.07419 0.0157 0.0051 1.0000
16.500 1.0599 0.08403 0.07975 0.0131 0.0051 1.0000
16.750 1.0506 0.08941 0.08523 0.0105 0.0051 1.0000
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Polar data table (+)
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