I.S.A. 960 (isa960-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 960 (isa960-il) Reynolds number: 50,000 Max Cl/Cd: 39.26 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa960-il-50000.txt Download as CSV file: xf-isa960-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 960
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3298 0.10300 0.09659 -0.0255 1.0000 0.1846
-8.750 -0.3443 0.10224 0.09599 -0.0255 1.0000 0.1898
-8.500 -0.3703 0.10270 0.09667 -0.0265 1.0000 0.1913
-8.250 -0.3426 0.09639 0.09033 -0.0226 1.0000 0.2020
-8.000 -0.3647 0.09620 0.09034 -0.0231 1.0000 0.2060
-7.750 -0.3549 0.09197 0.08617 -0.0200 1.0000 0.2128
-7.500 -0.3668 0.09072 0.08504 -0.0195 1.0000 0.2202
-7.250 -0.3755 0.08845 0.08289 -0.0189 1.0000 0.2247
-7.000 -0.3736 0.08577 0.08027 -0.0160 1.0000 0.2331
-6.750 -0.3854 0.08411 0.07870 -0.0174 1.0000 0.2397
-6.500 -0.3817 0.08116 0.07579 -0.0138 1.0000 0.2477
-6.250 -0.3861 0.07883 0.07352 -0.0143 1.0000 0.2567
-6.000 -0.3870 0.07683 0.07153 -0.0159 1.0000 0.2700
-5.750 -0.3841 0.07440 0.06911 -0.0157 1.0000 0.2850
-5.500 -0.3809 0.07143 0.06620 -0.0131 1.0000 0.3013
-5.250 -0.3775 0.06864 0.06348 -0.0096 1.0000 0.3199
-5.000 -0.3731 0.06624 0.06110 -0.0089 1.0000 0.3481
-4.750 -0.3688 0.06379 0.05870 -0.0065 1.0000 0.3789
-4.000 -0.1954 0.04329 0.03563 -0.0488 1.0000 0.1752
-3.750 -0.1675 0.04039 0.03244 -0.0504 1.0000 0.1786
-3.500 -0.1399 0.03825 0.02999 -0.0516 1.0000 0.1863
-3.250 -0.1081 0.03584 0.02704 -0.0533 1.0000 0.1947
-3.000 -0.0821 0.03445 0.02543 -0.0539 1.0000 0.2141
-2.750 -0.0539 0.03325 0.02379 -0.0548 1.0000 0.2374
-2.500 -0.0325 0.03273 0.02330 -0.0548 1.0000 0.2665
-2.250 -0.0064 0.03219 0.02253 -0.0556 0.9994 0.2856
-2.000 0.0749 0.03125 0.02126 -0.0656 0.9776 0.3101
-1.750 0.1328 0.03075 0.02044 -0.0712 0.9626 0.3308
-1.500 0.1853 0.03019 0.01985 -0.0757 0.9486 0.3632
-1.250 0.2355 0.02948 0.01933 -0.0797 0.9346 0.4098
-1.000 0.2769 0.02725 0.01887 -0.0812 0.9228 0.6891
-0.750 0.3275 0.02717 0.01814 -0.0845 0.9044 1.0000
-0.500 0.3755 0.02723 0.01783 -0.0876 0.8876 1.0000
-0.250 0.4193 0.02726 0.01760 -0.0900 0.8719 1.0000
0.000 0.4614 0.02721 0.01737 -0.0919 0.8567 1.0000
0.250 0.5021 0.02702 0.01704 -0.0933 0.8410 1.0000
0.500 0.5412 0.02669 0.01660 -0.0941 0.8250 1.0000
0.750 0.5789 0.02625 0.01607 -0.0945 0.8089 1.0000
1.000 0.6136 0.02587 0.01563 -0.0944 0.7934 1.0000
1.250 0.6448 0.02567 0.01538 -0.0940 0.7786 1.0000
1.500 0.6743 0.02556 0.01524 -0.0935 0.7642 1.0000
1.750 0.7046 0.02536 0.01501 -0.0929 0.7492 1.0000
2.000 0.7349 0.02509 0.01473 -0.0921 0.7336 1.0000
2.250 0.7647 0.02486 0.01448 -0.0913 0.7176 1.0000
2.500 0.7905 0.02489 0.01451 -0.0902 0.7002 1.0000
2.750 0.8155 0.02498 0.01464 -0.0890 0.6819 1.0000
3.000 0.8410 0.02503 0.01472 -0.0879 0.6631 1.0000
3.250 0.8674 0.02501 0.01471 -0.0868 0.6438 1.0000
3.500 0.8933 0.02500 0.01470 -0.0856 0.6235 1.0000
3.750 0.9167 0.02512 0.01489 -0.0843 0.6003 1.0000
4.000 0.9427 0.02514 0.01488 -0.0831 0.5776 1.0000
4.250 0.9678 0.02529 0.01498 -0.0819 0.5532 1.0000
4.500 0.9917 0.02556 0.01520 -0.0806 0.5270 1.0000
4.750 1.0168 0.02590 0.01542 -0.0795 0.5026 1.0000
5.000 1.0400 0.02654 0.01603 -0.0786 0.4792 1.0000
5.250 1.0654 0.02716 0.01654 -0.0778 0.4590 1.0000
5.500 1.0859 0.02794 0.01738 -0.0766 0.4364 1.0000
5.750 1.1088 0.02870 0.01810 -0.0756 0.4167 1.0000
6.000 1.1328 0.02950 0.01881 -0.0748 0.3981 1.0000
6.250 1.1536 0.03056 0.01994 -0.0738 0.3788 1.0000
6.500 1.1759 0.03169 0.02112 -0.0729 0.3607 1.0000
6.750 1.1993 0.03299 0.02243 -0.0722 0.3450 1.0000
7.000 1.2233 0.03447 0.02396 -0.0718 0.3323 1.0000
7.250 1.2499 0.03592 0.02539 -0.0717 0.3225 1.0000
7.500 1.2696 0.03773 0.02751 -0.0709 0.3139 1.0000
7.750 1.2956 0.03941 0.02926 -0.0709 0.3078 1.0000
8.000 1.3104 0.04175 0.03202 -0.0698 0.3030 1.0000
8.250 1.3281 0.04403 0.03461 -0.0690 0.2992 1.0000
8.500 1.3481 0.04629 0.03715 -0.0685 0.2960 1.0000
8.750 1.3612 0.04893 0.04011 -0.0673 0.2926 1.0000
9.000 1.3583 0.05235 0.04402 -0.0648 0.2889 1.0000
9.250 1.3843 0.05299 0.04469 -0.0642 0.2775 1.0000
9.500 1.3998 0.05341 0.04517 -0.0625 0.2619 1.0000
9.750 1.4096 0.05364 0.04549 -0.0601 0.2443 1.0000
10.000 1.4313 0.05190 0.04354 -0.0584 0.2197 1.0000
10.250 1.2735 0.07349 0.06641 -0.0513 0.2696 1.0000
10.500 1.2514 0.07892 0.07193 -0.0503 0.2664 1.0000
10.750 1.2265 0.08578 0.07885 -0.0506 0.2645 1.0000
11.000 1.2433 0.08448 0.07770 -0.0478 0.2472 1.0000
11.500 1.4230 0.06320 0.05415 -0.0388 0.1069 1.0000
11.750 1.4043 0.06701 0.05838 -0.0354 0.1040 1.0000
12.000 1.3830 0.07096 0.06273 -0.0328 0.1020 1.0000
12.250 1.3660 0.07532 0.06739 -0.0311 0.0992 1.0000
12.500 1.3636 0.07983 0.07198 -0.0302 0.0944 1.0000
12.750 1.3377 0.08486 0.07733 -0.0296 0.0941 1.0000
13.000 1.3115 0.09056 0.08330 -0.0300 0.0942 1.0000
13.250 1.2852 0.09693 0.08992 -0.0314 0.0944 1.0000
13.500 1.2585 0.10400 0.09719 -0.0336 0.0948 1.0000
13.750 1.2327 0.11172 0.10508 -0.0367 0.0953 1.0000
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Polar data table (+)
Polar graphs
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