SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7062 (14%) (sd7062-il) Reynolds number: 500,000 Max Cl/Cd: 94.55 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7062-il-500000-n5.txt Download as CSV file: xf-sd7062-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7062 (14%)
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5996 0.05550 0.05250 -0.0689 1.0000 0.0136
-11.750 -0.6390 0.04501 0.04177 -0.0782 1.0000 0.0135
-11.500 -0.6639 0.03928 0.03586 -0.0827 1.0000 0.0135
-11.250 -0.6684 0.03437 0.03066 -0.0892 0.9806 0.0135
-11.000 -0.6534 0.03100 0.02697 -0.0934 0.9614 0.0136
-10.750 -0.6346 0.02855 0.02422 -0.0957 0.9427 0.0138
-10.500 -0.6179 0.02675 0.02215 -0.0962 0.9223 0.0140
-10.250 -0.6023 0.02538 0.02052 -0.0956 0.9031 0.0141
-10.000 -0.5855 0.02425 0.01914 -0.0948 0.8859 0.0142
-9.750 -0.5693 0.02290 0.01759 -0.0939 0.8707 0.0144
-9.500 -0.5507 0.02179 0.01633 -0.0931 0.8569 0.0146
-9.250 -0.5303 0.02086 0.01526 -0.0924 0.8448 0.0147
-9.000 -0.5087 0.02006 0.01434 -0.0917 0.8334 0.0149
-8.750 -0.4862 0.01933 0.01349 -0.0912 0.8220 0.0151
-8.500 -0.4631 0.01862 0.01266 -0.0906 0.8120 0.0152
-8.250 -0.4395 0.01797 0.01189 -0.0901 0.8016 0.0154
-8.000 -0.4153 0.01734 0.01114 -0.0897 0.7921 0.0156
-7.750 -0.3909 0.01675 0.01043 -0.0892 0.7824 0.0159
-7.500 -0.3659 0.01617 0.00976 -0.0888 0.7731 0.0161
-7.000 -0.3151 0.01514 0.00853 -0.0881 0.7546 0.0166
-6.750 -0.2894 0.01469 0.00797 -0.0877 0.7456 0.0169
-6.500 -0.2631 0.01426 0.00746 -0.0874 0.7365 0.0171
-6.250 -0.2371 0.01383 0.00693 -0.0870 0.7277 0.0174
-6.000 -0.2110 0.01334 0.00641 -0.0868 0.7186 0.0178
-5.750 -0.1845 0.01299 0.00600 -0.0865 0.7099 0.0182
-5.500 -0.1573 0.01268 0.00564 -0.0863 0.7007 0.0188
-5.250 -0.1303 0.01240 0.00529 -0.0861 0.6920 0.0194
-5.000 -0.1029 0.01212 0.00495 -0.0859 0.6828 0.0200
-4.750 -0.0756 0.01188 0.00463 -0.0857 0.6741 0.0205
-4.500 -0.0482 0.01158 0.00429 -0.0855 0.6647 0.0211
-4.250 -0.0207 0.01135 0.00401 -0.0853 0.6559 0.0219
-4.000 0.0070 0.01115 0.00376 -0.0852 0.6464 0.0229
-3.750 0.0348 0.01099 0.00353 -0.0850 0.6374 0.0240
-3.500 0.0626 0.01080 0.00331 -0.0849 0.6279 0.0257
-3.250 0.0905 0.01064 0.00312 -0.0847 0.6188 0.0287
-3.000 0.1182 0.01046 0.00293 -0.0846 0.6091 0.0356
-2.750 0.1460 0.01026 0.00277 -0.0845 0.5999 0.0515
-2.500 0.1736 0.01009 0.00263 -0.0843 0.5903 0.0718
-2.250 0.2015 0.00992 0.00252 -0.0843 0.5809 0.0959
-2.000 0.2290 0.00977 0.00242 -0.0842 0.5711 0.1244
-1.750 0.2568 0.00956 0.00233 -0.0842 0.5615 0.1671
-1.500 0.2842 0.00935 0.00227 -0.0841 0.5522 0.2237
-1.250 0.3118 0.00916 0.00222 -0.0841 0.5425 0.2791
-1.000 0.3393 0.00900 0.00220 -0.0840 0.5332 0.3371
-0.750 0.3669 0.00888 0.00219 -0.0839 0.5232 0.3893
-0.500 0.3946 0.00879 0.00220 -0.0838 0.5140 0.4374
-0.250 0.4222 0.00876 0.00222 -0.0837 0.5042 0.4766
0.000 0.4500 0.00874 0.00225 -0.0835 0.4948 0.5096
0.250 0.4775 0.00875 0.00229 -0.0833 0.4853 0.5414
0.500 0.5052 0.00874 0.00233 -0.0832 0.4754 0.5737
0.750 0.5326 0.00877 0.00238 -0.0830 0.4663 0.6034
1.000 0.5600 0.00880 0.00244 -0.0828 0.4562 0.6307
1.250 0.5873 0.00884 0.00251 -0.0825 0.4471 0.6586
1.500 0.6142 0.00889 0.00259 -0.0822 0.4372 0.6864
2.250 0.6939 0.00903 0.00287 -0.0810 0.4098 0.7779
2.500 0.7191 0.00910 0.00298 -0.0803 0.4010 0.8119
2.750 0.7438 0.00913 0.00308 -0.0794 0.3921 0.8494
3.000 0.7668 0.00918 0.00319 -0.0782 0.3837 0.8934
3.250 0.7954 0.00922 0.00327 -0.0781 0.3747 0.9507
3.500 0.8295 0.00938 0.00337 -0.0795 0.3652 1.0000
3.750 0.8563 0.00957 0.00349 -0.0792 0.3561 1.0000
4.000 0.8829 0.00975 0.00363 -0.0790 0.3482 1.0000
4.250 0.9093 0.00995 0.00377 -0.0788 0.3391 1.0000
4.500 0.9357 0.01015 0.00393 -0.0785 0.3310 1.0000
4.750 0.9617 0.01037 0.00409 -0.0782 0.3222 1.0000
5.000 0.9878 0.01058 0.00426 -0.0779 0.3144 1.0000
5.250 1.0134 0.01081 0.00445 -0.0776 0.3057 1.0000
5.500 1.0392 0.01103 0.00464 -0.0773 0.2981 1.0000
5.750 1.0644 0.01129 0.00485 -0.0769 0.2895 1.0000
6.000 1.0898 0.01153 0.00506 -0.0765 0.2823 1.0000
6.250 1.1145 0.01180 0.00529 -0.0760 0.2742 1.0000
6.500 1.1393 0.01205 0.00553 -0.0756 0.2669 1.0000
6.750 1.1635 0.01234 0.00578 -0.0750 0.2590 1.0000
7.000 1.1877 0.01262 0.00604 -0.0745 0.2521 1.0000
7.250 1.2114 0.01291 0.00631 -0.0739 0.2447 1.0000
7.500 1.2346 0.01322 0.00661 -0.0732 0.2381 1.0000
7.750 1.2579 0.01352 0.00689 -0.0726 0.2311 1.0000
8.000 1.2798 0.01388 0.00722 -0.0717 0.2243 1.0000
8.250 1.3024 0.01418 0.00754 -0.0710 0.2179 1.0000
8.500 1.3230 0.01458 0.00790 -0.0700 0.2112 1.0000
8.750 1.3445 0.01491 0.00824 -0.0691 0.2052 1.0000
9.000 1.3644 0.01530 0.00863 -0.0679 0.1990 1.0000
9.250 1.3822 0.01569 0.00902 -0.0665 0.1936 1.0000
9.500 1.3997 0.01608 0.00942 -0.0649 0.1875 1.0000
9.750 1.4145 0.01658 0.00990 -0.0630 0.1818 1.0000
10.000 1.4314 0.01701 0.01035 -0.0615 0.1768 1.0000
10.250 1.4465 0.01753 0.01087 -0.0598 0.1711 1.0000
10.500 1.4603 0.01812 0.01147 -0.0580 0.1661 1.0000
10.750 1.4757 0.01866 0.01205 -0.0565 0.1611 1.0000
11.000 1.4885 0.01935 0.01274 -0.0548 0.1558 1.0000
11.250 1.5015 0.02007 0.01347 -0.0532 0.1511 1.0000
11.500 1.5147 0.02080 0.01423 -0.0517 0.1463 1.0000
11.750 1.5252 0.02172 0.01516 -0.0501 0.1414 1.0000
12.000 1.5373 0.02259 0.01607 -0.0487 0.1373 1.0000
12.250 1.5483 0.02356 0.01707 -0.0474 0.1326 1.0000
12.500 1.5563 0.02477 0.01829 -0.0459 0.1278 1.0000
12.750 1.5673 0.02584 0.01942 -0.0447 0.1241 1.0000
13.000 1.5763 0.02708 0.02069 -0.0436 0.1199 1.0000
13.250 1.5830 0.02856 0.02219 -0.0424 0.1161 1.0000
13.500 1.5913 0.02996 0.02365 -0.0414 0.1127 1.0000
13.750 1.5986 0.03148 0.02522 -0.0405 0.1090 1.0000
14.000 1.6035 0.03327 0.02704 -0.0396 0.1054 1.0000
14.250 1.6082 0.03515 0.02897 -0.0388 0.1021 1.0000
14.500 1.6139 0.03697 0.03086 -0.0382 0.0990 1.0000
14.750 1.6172 0.03908 0.03302 -0.0377 0.0959 1.0000
15.000 1.6174 0.04157 0.03555 -0.0372 0.0927 1.0000
15.250 1.6214 0.04377 0.03783 -0.0369 0.0902 1.0000
15.500 1.6234 0.04622 0.04035 -0.0367 0.0874 1.0000
15.750 1.6235 0.04899 0.04317 -0.0367 0.0847 1.0000
16.000 1.6205 0.05219 0.04642 -0.0369 0.0821 1.0000
16.250 1.6222 0.05493 0.04926 -0.0371 0.0800 1.0000
16.500 1.6215 0.05803 0.05244 -0.0375 0.0776 1.0000
16.750 1.6185 0.06151 0.05599 -0.0380 0.0753 1.0000
17.000 1.6125 0.06546 0.06000 -0.0388 0.0729 1.0000
17.250 1.6104 0.06897 0.06361 -0.0396 0.0711 1.0000
17.500 1.6072 0.07273 0.06746 -0.0406 0.0690 1.0000
17.750 1.6015 0.07692 0.07173 -0.0417 0.0669 1.0000
18.000 1.5935 0.08149 0.07638 -0.0431 0.0650 1.0000
18.250 1.5862 0.08608 0.08105 -0.0447 0.0634 1.0000
18.500 1.5821 0.09026 0.08534 -0.0461 0.0617 1.0000
18.750 1.5758 0.09481 0.08998 -0.0478 0.0600 1.0000
19.000 1.5673 0.09979 0.09504 -0.0497 0.0583 1.0000
19.250 1.5571 0.10513 0.10045 -0.0519 0.0566 1.0000
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Polar data table (+)
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