RAF 15 AIRFOIL (raf15-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAF 15 AIRFOIL (raf15-il) Reynolds number: 50,000 Max Cl/Cd: 32.54 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-raf15-il-50000.txt Download as CSV file: xf-raf15-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RAF 15 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5005 0.10479 0.09773 -0.0006 1.0000 0.1943
-8.000 -0.4977 0.10170 0.09470 -0.0003 1.0000 0.2023
-7.750 -0.5213 0.10128 0.09444 -0.0021 1.0000 0.2054
-7.500 -0.4979 0.09529 0.08844 -0.0001 1.0000 0.2122
-7.250 -0.5109 0.09364 0.08690 -0.0012 1.0000 0.2192
-7.000 -0.5043 0.08940 0.08271 -0.0005 1.0000 0.2242
-6.750 -0.5074 0.08692 0.08027 -0.0012 1.0000 0.2337
-6.500 -0.5005 0.08283 0.07623 -0.0003 1.0000 0.2396
-6.250 -0.5085 0.08134 0.07476 -0.0028 1.0000 0.2501
-6.000 -0.4929 0.07630 0.06978 0.0004 1.0000 0.2588
-5.750 -0.4891 0.07294 0.06646 0.0010 1.0000 0.2714
-5.500 -0.4845 0.06973 0.06328 0.0019 1.0000 0.2860
-5.250 -0.4807 0.06681 0.06038 0.0027 1.0000 0.3055
-5.000 -0.4766 0.06360 0.05719 0.0039 1.0000 0.3251
-4.750 -0.4681 0.06009 0.05373 0.0063 1.0000 0.3436
-4.500 -0.4634 0.05694 0.05061 0.0087 1.0000 0.3713
-4.250 -0.4580 0.05372 0.04746 0.0121 1.0000 0.4027
-4.000 -0.3853 0.04485 0.03676 -0.0094 1.0000 0.1593
-3.750 -0.3663 0.04055 0.03176 -0.0086 1.0000 0.1475
-3.500 -0.3480 0.03745 0.02833 -0.0070 1.0000 0.1466
-3.250 -0.3286 0.03446 0.02502 -0.0053 1.0000 0.1452
-3.000 -0.3077 0.03167 0.02163 -0.0035 1.0000 0.1471
-2.750 -0.2876 0.03006 0.02003 -0.0019 1.0000 0.1564
-2.500 -0.2640 0.02775 0.01714 -0.0003 1.0000 0.1622
-2.250 -0.2406 0.02627 0.01542 0.0011 1.0000 0.1759
-2.000 -0.2173 0.02494 0.01407 0.0024 1.0000 0.1958
-1.750 -0.1915 0.02341 0.01239 0.0035 1.0000 0.2311
-1.500 -0.1596 0.02174 0.01068 0.0034 1.0000 0.3088
-1.250 -0.1264 0.02027 0.00945 0.0024 1.0000 0.3969
-1.000 0.0111 0.01659 0.00776 -0.0189 1.0000 1.0000
-0.750 0.0373 0.01671 0.00742 -0.0182 1.0000 1.0000
-0.500 0.0601 0.01681 0.00716 -0.0170 1.0000 1.0000
-0.250 0.0813 0.01691 0.00702 -0.0156 1.0000 1.0000
0.000 0.1015 0.01703 0.00696 -0.0141 1.0000 1.0000
0.250 0.1211 0.01717 0.00696 -0.0126 1.0000 1.0000
0.500 0.1401 0.01734 0.00703 -0.0111 1.0000 1.0000
0.750 0.1586 0.01755 0.00718 -0.0095 1.0000 1.0000
1.000 0.1763 0.01780 0.00740 -0.0079 1.0000 1.0000
1.250 0.1929 0.01812 0.00772 -0.0063 1.0000 1.0000
1.500 0.2079 0.01853 0.00816 -0.0047 1.0000 1.0000
1.750 0.2202 0.01912 0.00879 -0.0031 1.0000 1.0000
2.000 0.2270 0.02005 0.00980 -0.0014 1.0000 1.0000
2.250 0.3376 0.02068 0.01076 -0.0201 0.9439 1.0000
2.500 0.4843 0.01904 0.00958 -0.0407 0.8598 1.0000
2.750 0.5748 0.01836 0.00875 -0.0498 0.7545 1.0000
3.000 0.6126 0.01894 0.00898 -0.0501 0.6867 1.0000
3.250 0.6417 0.01972 0.00955 -0.0494 0.6371 1.0000
3.500 0.6683 0.02054 0.01022 -0.0484 0.5959 1.0000
3.750 0.6927 0.02139 0.01098 -0.0472 0.5602 1.0000
4.000 0.7154 0.02228 0.01181 -0.0457 0.5272 1.0000
4.250 0.7375 0.02322 0.01276 -0.0440 0.4965 1.0000
4.500 0.7586 0.02418 0.01370 -0.0422 0.4665 1.0000
4.750 0.7788 0.02519 0.01470 -0.0402 0.4372 1.0000
5.000 0.7983 0.02619 0.01568 -0.0381 0.4073 1.0000
5.250 0.8165 0.02713 0.01662 -0.0357 0.3757 1.0000
5.500 0.8340 0.02799 0.01737 -0.0332 0.3424 1.0000
5.750 0.8519 0.02887 0.01806 -0.0308 0.3090 1.0000
6.000 0.8667 0.02998 0.01924 -0.0279 0.2755 1.0000
6.250 0.8827 0.03121 0.02048 -0.0253 0.2446 1.0000
6.500 0.9000 0.03243 0.02164 -0.0229 0.2187 1.0000
6.750 0.9167 0.03451 0.02397 -0.0206 0.2010 1.0000
7.000 0.9334 0.03662 0.02627 -0.0185 0.1874 1.0000
7.250 0.9497 0.03858 0.02834 -0.0164 0.1751 1.0000
7.500 0.9645 0.04103 0.03107 -0.0143 0.1664 1.0000
7.750 0.9752 0.04435 0.03478 -0.0119 0.1618 1.0000
8.000 0.9765 0.04840 0.03944 -0.0088 0.1587 1.0000
8.250 0.9793 0.05203 0.04345 -0.0063 0.1546 1.0000
8.500 0.9919 0.05472 0.04618 -0.0045 0.1483 1.0000
8.750 0.9826 0.05964 0.05155 -0.0018 0.1478 1.0000
9.000 0.9719 0.06485 0.05708 0.0002 0.1482 1.0000
9.250 0.9615 0.07013 0.06256 0.0017 0.1490 1.0000
9.500 0.8849 0.08075 0.07336 0.0004 0.1598 1.0000
9.750 0.8341 0.09277 0.08526 -0.0073 0.1751 1.0000
10.000 0.8282 0.09907 0.09155 -0.0097 0.1789 1.0000
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Polar data table (+)
Polar graphs
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