I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 961 (isa961-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.89 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa961-il-1000000-n5.txt Download as CSV file: xf-isa961-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 961
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5208 0.06060 0.05886 -0.0610 0.9875 0.0042
-10.500 -0.5466 0.02593 0.02313 -0.0974 0.9578 0.0041
-10.250 -0.5234 0.02239 0.01923 -0.0993 0.9465 0.0042
-10.000 -0.4993 0.02038 0.01694 -0.1000 0.9351 0.0042
-9.750 -0.4753 0.01896 0.01529 -0.1001 0.9240 0.0043
-9.500 -0.4525 0.01732 0.01338 -0.0999 0.9147 0.0044
-9.250 -0.4289 0.01596 0.01178 -0.0997 0.9068 0.0046
-9.000 -0.4037 0.01507 0.01075 -0.0995 0.9000 0.0047
-8.750 -0.3778 0.01439 0.00993 -0.0993 0.8934 0.0048
-8.500 -0.3515 0.01379 0.00921 -0.0991 0.8876 0.0050
-8.250 -0.3250 0.01320 0.00851 -0.0988 0.8815 0.0051
-8.000 -0.2984 0.01267 0.00786 -0.0986 0.8756 0.0053
-7.750 -0.2718 0.01218 0.00725 -0.0983 0.8663 0.0055
-7.500 -0.2451 0.01171 0.00665 -0.0980 0.8564 0.0057
-7.250 -0.2182 0.01129 0.00611 -0.0977 0.8474 0.0060
-7.000 -0.1908 0.01092 0.00565 -0.0975 0.8384 0.0062
-6.750 -0.1635 0.01064 0.00527 -0.0973 0.8279 0.0064
-6.500 -0.1368 0.01013 0.00464 -0.0970 0.8141 0.0071
-6.250 -0.1098 0.00986 0.00425 -0.0966 0.7960 0.0075
-6.000 -0.0831 0.00965 0.00390 -0.0962 0.7717 0.0079
-5.750 -0.0563 0.00948 0.00357 -0.0958 0.7449 0.0084
-5.500 -0.0293 0.00933 0.00328 -0.0955 0.7213 0.0090
-5.250 -0.0022 0.00919 0.00301 -0.0952 0.6987 0.0095
-5.000 0.0250 0.00899 0.00269 -0.0949 0.6783 0.0108
-4.750 0.0524 0.00887 0.00247 -0.0947 0.6571 0.0123
-4.500 0.0796 0.00883 0.00228 -0.0945 0.6325 0.0134
-4.250 0.1066 0.00877 0.00209 -0.0942 0.6031 0.0169
-4.000 0.1329 0.00859 0.00188 -0.0939 0.5686 0.0408
-3.750 0.1592 0.00870 0.00188 -0.0936 0.5221 0.0568
-3.500 0.1848 0.00897 0.00191 -0.0931 0.4589 0.0623
-3.250 0.2111 0.00921 0.00193 -0.0928 0.4101 0.0652
-3.000 0.2381 0.00937 0.00194 -0.0926 0.3791 0.0667
-2.750 0.2653 0.00943 0.00189 -0.0924 0.3545 0.0688
-2.500 0.2921 0.00953 0.00186 -0.0922 0.3224 0.0728
-2.250 0.3182 0.00976 0.00188 -0.0919 0.2753 0.0748
-2.000 0.3450 0.00990 0.00188 -0.0917 0.2471 0.0759
-1.750 0.3717 0.01005 0.00190 -0.0915 0.2213 0.0772
-1.500 0.3986 0.01020 0.00192 -0.0913 0.1982 0.0782
-1.250 0.4235 0.01059 0.00204 -0.0908 0.1296 0.0789
-0.750 0.4782 0.01076 0.00211 -0.0906 0.1132 0.0807
-0.500 0.5057 0.01081 0.00214 -0.0905 0.1106 0.0836
-0.250 0.5331 0.01086 0.00218 -0.0904 0.1086 0.0876
0.000 0.5605 0.01092 0.00224 -0.0903 0.1065 0.0926
0.250 0.5877 0.01093 0.00234 -0.0903 0.1039 0.1289
0.500 0.6150 0.01100 0.00243 -0.0902 0.1016 0.1441
0.750 0.6423 0.01107 0.00251 -0.0901 0.1001 0.1532
1.000 0.6697 0.01113 0.00259 -0.0901 0.0996 0.1617
1.250 0.6970 0.01120 0.00268 -0.0900 0.0990 0.1699
1.750 0.7513 0.01133 0.00287 -0.0899 0.0962 0.1992
2.000 0.7782 0.01137 0.00301 -0.0899 0.0935 0.2460
2.250 0.8045 0.01142 0.00316 -0.0898 0.0888 0.3157
2.750 0.8571 0.01050 0.00364 -0.0899 0.0584 1.0000
3.000 0.8831 0.01072 0.00382 -0.0896 0.0541 1.0000
3.250 0.9093 0.01091 0.00399 -0.0894 0.0515 1.0000
3.500 0.9354 0.01109 0.00416 -0.0892 0.0506 1.0000
3.750 0.9615 0.01127 0.00434 -0.0890 0.0501 1.0000
4.000 0.9875 0.01147 0.00454 -0.0888 0.0496 1.0000
4.250 1.0133 0.01167 0.00475 -0.0885 0.0491 1.0000
4.500 1.0390 0.01188 0.00496 -0.0883 0.0486 1.0000
4.750 1.0645 0.01210 0.00519 -0.0880 0.0481 1.0000
5.000 1.0898 0.01234 0.00544 -0.0877 0.0470 1.0000
5.250 1.1146 0.01262 0.00572 -0.0873 0.0454 1.0000
5.500 1.1389 0.01294 0.00604 -0.0869 0.0431 1.0000
5.750 1.1634 0.01322 0.00633 -0.0865 0.0418 1.0000
6.000 1.1885 0.01342 0.00655 -0.0862 0.0410 1.0000
6.250 1.2133 0.01365 0.00678 -0.0859 0.0395 1.0000
6.500 1.2373 0.01395 0.00705 -0.0855 0.0363 1.0000
6.750 1.2594 0.01440 0.00739 -0.0848 0.0210 1.0000
7.000 1.2806 0.01494 0.00791 -0.0839 0.0122 1.0000
7.250 1.3026 0.01538 0.00839 -0.0831 0.0100 1.0000
7.500 1.3243 0.01581 0.00886 -0.0823 0.0084 1.0000
7.750 1.3460 0.01623 0.00931 -0.0816 0.0074 1.0000
8.000 1.3666 0.01671 0.00981 -0.0806 0.0065 1.0000
8.250 1.3870 0.01718 0.01033 -0.0796 0.0059 1.0000
8.500 1.4072 0.01764 0.01083 -0.0787 0.0055 1.0000
8.750 1.4264 0.01814 0.01138 -0.0775 0.0051 1.0000
9.000 1.4442 0.01869 0.01197 -0.0762 0.0047 1.0000
9.250 1.4590 0.01935 0.01267 -0.0743 0.0042 1.0000
9.500 1.4739 0.01991 0.01328 -0.0725 0.0040 1.0000
9.750 1.4884 0.02051 0.01393 -0.0706 0.0038 1.0000
10.000 1.5019 0.02118 0.01466 -0.0687 0.0036 1.0000
10.250 1.5149 0.02191 0.01545 -0.0668 0.0034 1.0000
10.500 1.5272 0.02270 0.01629 -0.0650 0.0033 1.0000
10.750 1.5386 0.02358 0.01722 -0.0631 0.0031 1.0000
11.000 1.5484 0.02459 0.01832 -0.0612 0.0030 1.0000
11.250 1.5557 0.02583 0.01964 -0.0591 0.0028 1.0000
11.500 1.5628 0.02714 0.02104 -0.0572 0.0027 1.0000
11.750 1.5709 0.02841 0.02240 -0.0555 0.0027 1.0000
12.000 1.5779 0.02983 0.02390 -0.0540 0.0026 1.0000
12.250 1.5835 0.03141 0.02557 -0.0524 0.0025 1.0000
12.500 1.5882 0.03314 0.02740 -0.0510 0.0025 1.0000
12.750 1.5919 0.03505 0.02940 -0.0497 0.0024 1.0000
13.000 1.5942 0.03716 0.03161 -0.0486 0.0023 1.0000
13.250 1.5961 0.03941 0.03396 -0.0477 0.0022 1.0000
13.500 1.5967 0.04190 0.03655 -0.0470 0.0022 1.0000
13.750 1.5962 0.04459 0.03934 -0.0464 0.0021 1.0000
14.000 1.5949 0.04750 0.04235 -0.0461 0.0021 1.0000
14.250 1.5924 0.05069 0.04564 -0.0460 0.0020 1.0000
14.500 1.5880 0.05425 0.04931 -0.0462 0.0020 1.0000
14.750 1.5823 0.05813 0.05330 -0.0466 0.0019 1.0000
15.000 1.5743 0.06251 0.05779 -0.0474 0.0019 1.0000
15.250 1.5643 0.06737 0.06277 -0.0485 0.0019 1.0000
15.500 1.5521 0.07267 0.06819 -0.0498 0.0018 1.0000
15.750 1.5381 0.07844 0.07409 -0.0515 0.0018 1.0000
16.000 1.5222 0.08467 0.08045 -0.0534 0.0018 1.0000
16.250 1.5049 0.09119 0.08710 -0.0556 0.0018 1.0000
16.500 1.4867 0.09797 0.09401 -0.0579 0.0018 1.0000
16.750 1.4686 0.10485 0.10101 -0.0603 0.0018 1.0000
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Polar data table (+)
Polar graphs
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