I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 961 (isa961-il) Reynolds number: 500,000 Max Cl/Cd: 75.47 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa961-il-500000-n5.txt Download as CSV file: xf-isa961-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3623 0.08878 0.08662 -0.0348 1.0000 0.0066
-9.750 -0.3728 0.08456 0.08245 -0.0350 1.0000 0.0066
-9.250 -0.4163 0.02977 0.02665 -0.0941 0.9569 0.0062
-9.000 -0.3920 0.02467 0.02098 -0.0976 0.9499 0.0063
-8.750 -0.3662 0.02214 0.01806 -0.0989 0.9423 0.0064
-8.500 -0.3412 0.01957 0.01511 -0.0999 0.9354 0.0066
-8.250 -0.3152 0.01811 0.01342 -0.1002 0.9278 0.0068
-8.000 -0.2880 0.01707 0.01220 -0.1005 0.9214 0.0071
-7.750 -0.2615 0.01632 0.01131 -0.1004 0.9141 0.0074
-7.500 -0.2346 0.01556 0.01039 -0.1004 0.9076 0.0079
-7.250 -0.2081 0.01482 0.00949 -0.1002 0.9007 0.0083
-7.000 -0.1816 0.01410 0.00857 -0.0999 0.8933 0.0087
-6.750 -0.1552 0.01346 0.00777 -0.0995 0.8843 0.0090
-6.500 -0.1285 0.01296 0.00711 -0.0991 0.8746 0.0093
-6.250 -0.1025 0.01213 0.00613 -0.0987 0.8642 0.0100
-6.000 -0.0757 0.01164 0.00553 -0.0984 0.8542 0.0106
-5.750 -0.0487 0.01127 0.00504 -0.0980 0.8434 0.0115
-5.500 -0.0217 0.01096 0.00460 -0.0977 0.8312 0.0126
-5.250 0.0055 0.01069 0.00421 -0.0973 0.8181 0.0136
-5.000 0.0327 0.01030 0.00368 -0.0969 0.8046 0.0157
-4.750 0.0597 0.01002 0.00328 -0.0965 0.7888 0.0183
-4.500 0.0861 0.00962 0.00290 -0.0961 0.7700 0.0370
-4.250 0.1130 0.00957 0.00285 -0.0958 0.7483 0.0578
-4.000 0.1402 0.00964 0.00279 -0.0954 0.7272 0.0649
-3.750 0.1673 0.00966 0.00268 -0.0951 0.7065 0.0687
-3.500 0.1942 0.00961 0.00253 -0.0948 0.6847 0.0722
-3.250 0.2210 0.00962 0.00242 -0.0944 0.6619 0.0757
-3.000 0.2476 0.00969 0.00233 -0.0941 0.6350 0.0790
-2.750 0.2739 0.00975 0.00222 -0.0936 0.6035 0.0806
-2.500 0.3000 0.00977 0.00209 -0.0932 0.5704 0.0826
-2.250 0.3262 0.00984 0.00200 -0.0929 0.5362 0.0851
-2.000 0.3513 0.01004 0.00197 -0.0923 0.4864 0.0874
-1.750 0.3770 0.01022 0.00196 -0.0919 0.4471 0.0893
-1.500 0.4033 0.01036 0.00195 -0.0916 0.4180 0.0914
-1.250 0.4298 0.01049 0.00196 -0.0914 0.3932 0.0949
-1.000 0.4564 0.01058 0.00199 -0.0911 0.3705 0.1032
-0.750 0.4822 0.01074 0.00208 -0.0908 0.3365 0.1266
-0.500 0.5074 0.01102 0.00218 -0.0905 0.2933 0.1437
-0.250 0.5327 0.01131 0.00229 -0.0901 0.2554 0.1544
0.000 0.5585 0.01153 0.00239 -0.0898 0.2296 0.1651
0.250 0.5845 0.01172 0.00250 -0.0895 0.2100 0.1775
0.500 0.6108 0.01186 0.00261 -0.0893 0.1937 0.1919
0.750 0.6346 0.01230 0.00282 -0.0888 0.1333 0.2095
1.000 0.6604 0.01244 0.00299 -0.0885 0.1230 0.2452
1.250 0.6865 0.01249 0.00316 -0.0884 0.1167 0.3094
1.500 0.7080 0.01158 0.00338 -0.0876 0.1132 0.7424
2.000 0.7691 0.01148 0.00368 -0.0887 0.1084 1.0000
2.250 0.7952 0.01167 0.00384 -0.0885 0.1062 1.0000
2.500 0.8211 0.01188 0.00401 -0.0882 0.1039 1.0000
2.750 0.8469 0.01209 0.00420 -0.0879 0.1015 1.0000
3.000 0.8729 0.01228 0.00437 -0.0876 0.0997 1.0000
3.250 0.8990 0.01244 0.00453 -0.0874 0.0984 1.0000
3.500 0.9250 0.01262 0.00470 -0.0872 0.0963 1.0000
3.750 0.9507 0.01282 0.00489 -0.0869 0.0931 1.0000
4.000 0.9759 0.01306 0.00511 -0.0866 0.0886 1.0000
4.250 1.0015 0.01327 0.00532 -0.0863 0.0837 1.0000
4.500 1.0243 0.01376 0.00564 -0.0856 0.0598 1.0000
4.750 1.0486 0.01407 0.00595 -0.0852 0.0580 1.0000
5.000 1.0728 0.01438 0.00628 -0.0847 0.0565 1.0000
5.250 1.0971 0.01469 0.00660 -0.0842 0.0553 1.0000
5.500 1.1210 0.01501 0.00694 -0.0837 0.0539 1.0000
5.750 1.1443 0.01537 0.00733 -0.0831 0.0515 1.0000
6.000 1.1679 0.01569 0.00770 -0.0826 0.0498 1.0000
6.250 1.1912 0.01602 0.00807 -0.0821 0.0481 1.0000
6.500 1.2141 0.01638 0.00848 -0.0814 0.0462 1.0000
6.750 1.2358 0.01683 0.00895 -0.0806 0.0437 1.0000
7.000 1.2577 0.01724 0.00939 -0.0799 0.0413 1.0000
7.250 1.2806 0.01753 0.00972 -0.0793 0.0375 1.0000
7.500 1.2992 0.01818 0.01020 -0.0782 0.0171 1.0000
7.750 1.3176 0.01883 0.01089 -0.0769 0.0122 1.0000
8.000 1.3363 0.01941 0.01155 -0.0756 0.0108 1.0000
8.250 1.3529 0.02011 0.01233 -0.0740 0.0095 1.0000
8.500 1.3677 0.02082 0.01313 -0.0722 0.0085 1.0000
8.750 1.3825 0.02144 0.01382 -0.0703 0.0078 1.0000
9.000 1.3961 0.02214 0.01460 -0.0683 0.0072 1.0000
9.250 1.4086 0.02294 0.01550 -0.0663 0.0068 1.0000
9.500 1.4192 0.02389 0.01654 -0.0641 0.0063 1.0000
9.750 1.4285 0.02497 0.01772 -0.0619 0.0060 1.0000
10.000 1.4393 0.02596 0.01881 -0.0600 0.0058 1.0000
10.250 1.4488 0.02707 0.02002 -0.0581 0.0055 1.0000
10.500 1.4574 0.02830 0.02134 -0.0563 0.0053 1.0000
10.750 1.4651 0.02963 0.02276 -0.0546 0.0050 1.0000
11.000 1.4717 0.03110 0.02432 -0.0529 0.0047 1.0000
11.250 1.4771 0.03273 0.02604 -0.0514 0.0045 1.0000
11.500 1.4791 0.03473 0.02816 -0.0498 0.0044 1.0000
11.750 1.4767 0.03726 0.03081 -0.0482 0.0042 1.0000
12.000 1.4765 0.03971 0.03338 -0.0470 0.0041 1.0000
12.250 1.4760 0.04232 0.03612 -0.0462 0.0040 1.0000
12.500 1.4741 0.04521 0.03914 -0.0455 0.0040 1.0000
12.750 1.4706 0.04843 0.04250 -0.0452 0.0039 1.0000
13.000 1.4651 0.05206 0.04625 -0.0451 0.0038 1.0000
13.250 1.4588 0.05594 0.05027 -0.0454 0.0037 1.0000
13.500 1.4508 0.06025 0.05472 -0.0459 0.0037 1.0000
13.750 1.4416 0.06493 0.05954 -0.0468 0.0036 1.0000
14.000 1.4317 0.06989 0.06464 -0.0480 0.0036 1.0000
14.250 1.4210 0.07514 0.07002 -0.0494 0.0035 1.0000
14.500 1.4097 0.08062 0.07563 -0.0511 0.0035 1.0000
14.750 1.3975 0.08636 0.08151 -0.0529 0.0035 1.0000
15.000 1.3853 0.09216 0.08742 -0.0548 0.0034 1.0000
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Polar data table (+)
Polar graphs
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