I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: I.S.A. 961 (isa961-il) Reynolds number: 100,000 Max Cl/Cd: 53.94 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa961-il-100000-n5.txt Download as CSV file: xf-isa961-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3329 0.09245 0.08783 -0.0331 1.0000 0.0256
-8.750 -0.3416 0.09019 0.08568 -0.0318 1.0000 0.0253
-8.500 -0.3553 0.08839 0.08399 -0.0295 1.0000 0.0251
-8.250 -0.3680 0.08636 0.08206 -0.0277 1.0000 0.0249
-8.000 -0.3788 0.08401 0.07979 -0.0267 1.0000 0.0247
-7.750 -0.3707 0.07940 0.07521 -0.0314 0.9961 0.0247
-7.500 -0.3484 0.07303 0.06879 -0.0403 0.9890 0.0251
-7.250 -0.3238 0.06595 0.06162 -0.0498 0.9816 0.0256
-7.000 -0.2955 0.05813 0.05365 -0.0596 0.9750 0.0258
-6.750 -0.2669 0.04922 0.04446 -0.0687 0.9677 0.0257
-6.500 -0.2370 0.03376 0.02790 -0.0796 0.9615 0.0255
-6.250 -0.2062 0.02764 0.02070 -0.0828 0.9566 0.0264
-6.000 -0.1714 0.02492 0.01743 -0.0850 0.9531 0.0283
-5.750 -0.1406 0.02391 0.01628 -0.0860 0.9472 0.0318
-5.500 -0.1069 0.02219 0.01414 -0.0873 0.9425 0.0357
-5.250 -0.0698 0.02134 0.01317 -0.0892 0.9388 0.0419
-5.000 -0.0373 0.02086 0.01255 -0.0900 0.9329 0.0557
-4.750 -0.0031 0.02051 0.01200 -0.0911 0.9273 0.0744
-4.500 0.0339 0.02036 0.01160 -0.0930 0.9232 0.0925
-4.250 0.0637 0.02047 0.01162 -0.0934 0.9154 0.1065
-4.000 0.0995 0.02014 0.01129 -0.0949 0.9094 0.1145
-3.750 0.1323 0.01947 0.01038 -0.0955 0.9010 0.1184
-3.500 0.1676 0.01885 0.00967 -0.0966 0.8936 0.1227
-3.250 0.1973 0.01848 0.00923 -0.0967 0.8841 0.1280
-3.000 0.2312 0.01798 0.00857 -0.0975 0.8776 0.1331
-2.750 0.2585 0.01761 0.00822 -0.0972 0.8677 0.1376
-2.500 0.2894 0.01722 0.00778 -0.0974 0.8596 0.1446
-2.250 0.3182 0.01685 0.00739 -0.0972 0.8491 0.1532
-2.000 0.3455 0.01654 0.00709 -0.0968 0.8370 0.1669
-1.750 0.3733 0.01621 0.00678 -0.0964 0.8244 0.1847
-1.500 0.4007 0.01589 0.00646 -0.0958 0.8098 0.2060
-1.250 0.4281 0.01558 0.00616 -0.0952 0.7925 0.2311
-1.000 0.4559 0.01526 0.00586 -0.0947 0.7737 0.2649
-0.750 0.4825 0.01495 0.00564 -0.0941 0.7538 0.3225
-0.500 0.5191 0.01323 0.00547 -0.0953 0.7350 1.0000
-0.250 0.5458 0.01329 0.00533 -0.0947 0.7181 1.0000
0.000 0.5724 0.01336 0.00522 -0.0941 0.7001 1.0000
0.250 0.5988 0.01345 0.00512 -0.0935 0.6806 1.0000
0.500 0.6244 0.01358 0.00509 -0.0928 0.6587 1.0000
0.750 0.6502 0.01372 0.00505 -0.0921 0.6364 1.0000
1.000 0.6755 0.01389 0.00508 -0.0915 0.6133 1.0000
1.250 0.7009 0.01409 0.00513 -0.0908 0.5915 1.0000
1.500 0.7260 0.01431 0.00521 -0.0902 0.5692 1.0000
1.750 0.7509 0.01455 0.00532 -0.0895 0.5467 1.0000
2.000 0.7756 0.01482 0.00547 -0.0888 0.5244 1.0000
2.250 0.8000 0.01511 0.00563 -0.0882 0.5028 1.0000
2.500 0.8241 0.01543 0.00582 -0.0874 0.4815 1.0000
2.750 0.8475 0.01580 0.00606 -0.0866 0.4573 1.0000
3.000 0.8703 0.01621 0.00630 -0.0857 0.4319 1.0000
3.250 0.8925 0.01667 0.00658 -0.0848 0.4067 1.0000
3.500 0.9150 0.01710 0.00691 -0.0840 0.3817 1.0000
3.750 0.9375 0.01754 0.00724 -0.0832 0.3609 1.0000
4.000 0.9606 0.01794 0.00759 -0.0825 0.3438 1.0000
4.250 0.9839 0.01833 0.00798 -0.0818 0.3305 1.0000
4.500 1.0072 0.01872 0.00837 -0.0812 0.3185 1.0000
4.750 1.0304 0.01912 0.00878 -0.0805 0.3073 1.0000
5.000 1.0534 0.01953 0.00921 -0.0799 0.2969 1.0000
5.250 1.0757 0.01998 0.00969 -0.0791 0.2865 1.0000
5.500 1.0982 0.02041 0.01017 -0.0784 0.2758 1.0000
5.750 1.1202 0.02088 0.01067 -0.0776 0.2656 1.0000
6.250 1.1635 0.02185 0.01179 -0.0760 0.2468 1.0000
6.500 1.1842 0.02237 0.01237 -0.0751 0.2367 1.0000
6.750 1.2041 0.02295 0.01299 -0.0740 0.2258 1.0000
7.000 1.2248 0.02347 0.01363 -0.0731 0.2154 1.0000
7.250 1.2447 0.02404 0.01430 -0.0721 0.2062 1.0000
7.500 1.2635 0.02465 0.01505 -0.0710 0.1953 1.0000
7.750 1.2814 0.02532 0.01576 -0.0697 0.1719 1.0000
8.000 1.2914 0.02648 0.01664 -0.0677 0.1411 1.0000
8.250 1.3003 0.02777 0.01776 -0.0654 0.1260 1.0000
8.500 1.3099 0.02887 0.01888 -0.0632 0.1176 1.0000
8.750 1.3210 0.02987 0.01998 -0.0611 0.1108 1.0000
9.000 1.3316 0.03094 0.02116 -0.0591 0.1025 1.0000
9.250 1.3461 0.03174 0.02218 -0.0576 0.0944 1.0000
9.750 1.3548 0.03497 0.02527 -0.0532 0.0577 1.0000
10.000 1.3531 0.03714 0.02748 -0.0507 0.0520 1.0000
10.250 1.3592 0.03873 0.02928 -0.0490 0.0472 1.0000
10.750 1.3716 0.04208 0.03310 -0.0460 0.0345 1.0000
11.000 1.3685 0.04471 0.03572 -0.0445 0.0228 1.0000
11.250 1.3623 0.04781 0.03880 -0.0432 0.0208 1.0000
11.500 1.3556 0.05114 0.04223 -0.0423 0.0194 1.0000
11.750 1.3485 0.05472 0.04597 -0.0418 0.0185 1.0000
12.000 1.3407 0.05859 0.05001 -0.0417 0.0180 1.0000
12.250 1.3317 0.06283 0.05447 -0.0421 0.0177 1.0000
12.500 1.3211 0.06754 0.05939 -0.0429 0.0175 1.0000
12.750 1.3087 0.07274 0.06480 -0.0441 0.0173 1.0000
13.000 1.2952 0.07842 0.07068 -0.0458 0.0172 1.0000
13.250 1.2808 0.08453 0.07700 -0.0479 0.0171 1.0000
13.500 1.2657 0.09097 0.08363 -0.0502 0.0170 1.0000
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Polar data table (+)
Polar graphs
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