I.S.A. 962 (isa962-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 962 (isa962-il) Reynolds number: 100,000 Max Cl/Cd: 56.12 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa962-il-100000-n5.txt Download as CSV file: xf-isa962-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: I.S.A. 962
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3069 0.09515 0.09023 -0.0287 1.0000 0.0712
-8.500 -0.3223 0.09411 0.08931 -0.0264 1.0000 0.0722
-8.250 -0.3425 0.09334 0.08865 -0.0243 1.0000 0.0731
-8.000 -0.3178 0.08789 0.08309 -0.0441 0.9869 0.0745
-7.750 -0.3003 0.08360 0.07885 -0.0424 0.9837 0.0752
-7.500 -0.2817 0.08043 0.07570 -0.0417 0.9784 0.0766
-7.250 -0.2574 0.07710 0.07235 -0.0450 0.9728 0.0797
-6.750 -0.1958 0.06721 0.06218 -0.0663 0.9545 0.0866
-6.250 -0.1317 0.05146 0.04581 -0.0812 0.9412 0.0552
-6.000 -0.1048 0.04893 0.04325 -0.0831 0.9350 0.0541
-5.750 -0.0714 0.04487 0.03897 -0.0874 0.9300 0.0537
-5.500 -0.0425 0.04101 0.03482 -0.0904 0.9217 0.0538
-5.250 -0.0089 0.03749 0.03101 -0.0936 0.9166 0.0531
-5.000 0.0199 0.03436 0.02756 -0.0953 0.9087 0.0521
-4.750 0.0523 0.03120 0.02397 -0.0973 0.9026 0.0514
-4.500 0.0828 0.02865 0.02099 -0.0984 0.8956 0.0510
-4.250 0.1128 0.02659 0.01852 -0.0991 0.8880 0.0509
-4.000 0.1435 0.02491 0.01648 -0.0996 0.8806 0.0514
-3.750 0.1726 0.02366 0.01489 -0.0996 0.8714 0.0529
-3.500 0.2013 0.02255 0.01346 -0.0995 0.8620 0.0542
-3.250 0.2313 0.02151 0.01215 -0.0994 0.8531 0.0547
-3.000 0.2577 0.02066 0.01117 -0.0988 0.8419 0.0553
-2.750 0.2857 0.01987 0.01032 -0.0984 0.8323 0.0562
-2.500 0.3131 0.01922 0.00964 -0.0980 0.8221 0.0573
-2.250 0.3394 0.01870 0.00909 -0.0973 0.8109 0.0587
-2.000 0.3671 0.01820 0.00855 -0.0968 0.8009 0.0611
-1.750 0.3940 0.01778 0.00807 -0.0962 0.7896 0.0645
-1.500 0.4203 0.01740 0.00773 -0.0956 0.7771 0.0682
-1.250 0.4476 0.01705 0.00734 -0.0950 0.7659 0.0723
-1.000 0.4755 0.01674 0.00702 -0.0946 0.7559 0.0783
-0.750 0.5024 0.01650 0.00681 -0.0941 0.7447 0.0916
-0.500 0.5303 0.01614 0.00656 -0.0937 0.7351 0.1342
-0.250 0.5578 0.01568 0.00652 -0.0936 0.7243 0.2595
0.250 0.6188 0.01403 0.00632 -0.0938 0.6989 1.0000
0.750 0.6715 0.01422 0.00616 -0.0924 0.6680 1.0000
1.000 0.6976 0.01435 0.00613 -0.0917 0.6522 1.0000
1.250 0.7236 0.01449 0.00614 -0.0911 0.6358 1.0000
1.500 0.7491 0.01465 0.00618 -0.0904 0.6179 1.0000
1.750 0.7744 0.01483 0.00624 -0.0896 0.5978 1.0000
2.000 0.7995 0.01502 0.00632 -0.0888 0.5772 1.0000
2.250 0.8245 0.01524 0.00641 -0.0881 0.5569 1.0000
2.500 0.8491 0.01548 0.00653 -0.0873 0.5338 1.0000
2.750 0.8731 0.01575 0.00667 -0.0864 0.5076 1.0000
3.000 0.8969 0.01606 0.00684 -0.0856 0.4810 1.0000
3.250 0.9201 0.01642 0.00703 -0.0847 0.4550 1.0000
3.500 0.9434 0.01681 0.00729 -0.0838 0.4302 1.0000
3.750 0.9662 0.01724 0.00758 -0.0829 0.4084 1.0000
4.000 0.9888 0.01770 0.00791 -0.0820 0.3885 1.0000
4.250 1.0112 0.01819 0.00829 -0.0811 0.3699 1.0000
4.500 1.0333 0.01871 0.00870 -0.0802 0.3526 1.0000
4.750 1.0551 0.01924 0.00915 -0.0793 0.3362 1.0000
5.000 1.0767 0.01980 0.00964 -0.0784 0.3203 1.0000
5.250 1.0979 0.02036 0.01015 -0.0774 0.3041 1.0000
5.500 1.1189 0.02092 0.01067 -0.0765 0.2871 1.0000
5.750 1.1397 0.02148 0.01122 -0.0755 0.2696 1.0000
6.000 1.1601 0.02205 0.01178 -0.0744 0.2520 1.0000
6.250 1.1799 0.02265 0.01235 -0.0733 0.2355 1.0000
6.500 1.1990 0.02330 0.01296 -0.0722 0.2214 1.0000
6.750 1.2173 0.02400 0.01361 -0.0709 0.2099 1.0000
7.000 1.2351 0.02474 0.01430 -0.0696 0.2000 1.0000
7.250 1.2530 0.02550 0.01505 -0.0684 0.1919 1.0000
7.500 1.2693 0.02633 0.01584 -0.0669 0.1852 1.0000
7.750 1.2864 0.02716 0.01670 -0.0656 0.1793 1.0000
8.000 1.3029 0.02801 0.01758 -0.0642 0.1734 1.0000
8.250 1.3174 0.02901 0.01852 -0.0626 0.1686 1.0000
8.500 1.3338 0.02986 0.01947 -0.0612 0.1638 1.0000
8.750 1.3489 0.03076 0.02048 -0.0597 0.1594 1.0000
9.000 1.3632 0.03176 0.02149 -0.0581 0.1554 1.0000
9.250 1.3784 0.03287 0.02256 -0.0568 0.1517 1.0000
9.500 1.3931 0.03383 0.02371 -0.0553 0.1478 1.0000
9.750 1.4070 0.03487 0.02487 -0.0539 0.1440 1.0000
10.000 1.4210 0.03596 0.02604 -0.0525 0.1407 1.0000
10.250 1.4364 0.03713 0.02721 -0.0514 0.1378 1.0000
10.500 1.4503 0.03834 0.02856 -0.0501 0.1350 1.0000
10.750 1.4608 0.03957 0.03001 -0.0485 0.1318 1.0000
11.000 1.4702 0.04083 0.03143 -0.0470 0.1283 1.0000
11.250 1.4785 0.04208 0.03276 -0.0455 0.1250 1.0000
11.500 1.4873 0.04342 0.03409 -0.0442 0.1219 1.0000
11.750 1.4901 0.04507 0.03604 -0.0425 0.1185 1.0000
12.000 1.4937 0.04673 0.03790 -0.0411 0.1151 1.0000
12.250 1.4974 0.04840 0.03969 -0.0399 0.1121 1.0000
12.500 1.5015 0.05011 0.04148 -0.0389 0.1096 1.0000
12.750 1.5048 0.05214 0.04368 -0.0379 0.1073 1.0000
13.000 1.5054 0.05447 0.04627 -0.0371 0.1048 1.0000
13.250 1.5052 0.05689 0.04890 -0.0365 0.1021 1.0000
13.500 1.5043 0.05939 0.05154 -0.0360 0.0997 1.0000
13.750 1.5032 0.06195 0.05420 -0.0358 0.0975 1.0000
14.000 1.5009 0.06486 0.05726 -0.0357 0.0955 1.0000
14.250 1.4946 0.06848 0.06117 -0.0359 0.0932 1.0000
14.500 1.4873 0.07230 0.06522 -0.0364 0.0910 1.0000
14.750 1.4792 0.07635 0.06945 -0.0373 0.0887 1.0000
15.000 1.4711 0.08054 0.07376 -0.0386 0.0865 1.0000
15.250 1.4625 0.08496 0.07827 -0.0400 0.0844 1.0000
15.500 1.4457 0.09113 0.08474 -0.0422 0.0824 1.0000
15.750 1.4273 0.09783 0.09169 -0.0450 0.0807 1.0000
16.000 1.4066 0.10520 0.09928 -0.0483 0.0791 1.0000
16.250 1.3827 0.11352 0.10780 -0.0523 0.0779 1.0000
16.500 1.3506 0.12392 0.11840 -0.0577 0.0771 1.0000
17.000 1.3093 0.14072 0.13537 -0.0670 0.0740 1.0000
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Polar data table (+)
Polar graphs
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