I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: I.S.A. 961 (isa961-il) Reynolds number: 50,000 Max Cl/Cd: 39.48 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-isa961-il-50000-n5.txt Download as CSV file: xf-isa961-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3234 0.09949 0.09291 -0.0326 1.0000 0.0500
-8.750 -0.3290 0.09694 0.09049 -0.0320 1.0000 0.0493
-8.500 -0.3373 0.09462 0.08830 -0.0310 1.0000 0.0488
-8.250 -0.3451 0.09216 0.08597 -0.0304 1.0000 0.0484
-8.000 -0.3517 0.08955 0.08346 -0.0301 1.0000 0.0481
-7.750 -0.3575 0.08686 0.08086 -0.0301 1.0000 0.0480
-7.500 -0.3620 0.08401 0.07809 -0.0303 1.0000 0.0479
-7.250 -0.3644 0.08099 0.07512 -0.0308 1.0000 0.0480
-7.000 -0.3646 0.07775 0.07191 -0.0317 1.0000 0.0481
-6.750 -0.3621 0.07424 0.06841 -0.0330 1.0000 0.0482
-6.500 -0.3567 0.07043 0.06457 -0.0347 1.0000 0.0483
-6.250 -0.3479 0.06625 0.06033 -0.0370 1.0000 0.0483
-6.000 -0.3354 0.06172 0.05568 -0.0396 1.0000 0.0482
-5.750 -0.3144 0.05661 0.05036 -0.0437 0.9986 0.0486
-5.500 -0.2756 0.05010 0.04343 -0.0511 0.9934 0.0505
-5.250 -0.2318 0.04144 0.03379 -0.0592 0.9891 0.0549
-5.000 -0.1980 0.03990 0.03210 -0.0617 0.9832 0.0599
-4.750 -0.1568 0.03492 0.02616 -0.0660 0.9789 0.0684
-4.500 -0.1198 0.03292 0.02372 -0.0686 0.9734 0.0826
-4.250 -0.0834 0.03209 0.02260 -0.0708 0.9669 0.1041
-4.000 -0.0505 0.03207 0.02247 -0.0724 0.9590 0.1268
-3.750 -0.0114 0.03098 0.02098 -0.0749 0.9530 0.1411
-3.500 0.0241 0.02982 0.01926 -0.0765 0.9450 0.1488
-3.250 0.0642 0.02909 0.01834 -0.0791 0.9383 0.1583
-3.000 0.0985 0.02833 0.01726 -0.0803 0.9287 0.1649
-2.750 0.1413 0.02757 0.01632 -0.0830 0.9220 0.1716
-2.500 0.1759 0.02706 0.01554 -0.0841 0.9114 0.1800
-2.250 0.2148 0.02659 0.01493 -0.0860 0.9028 0.1938
-2.000 0.2541 0.02604 0.01434 -0.0880 0.8943 0.2084
-1.750 0.2885 0.02559 0.01387 -0.0891 0.8844 0.2264
-1.500 0.3295 0.02499 0.01333 -0.0913 0.8770 0.2563
-1.250 0.3593 0.02457 0.01309 -0.0916 0.8652 0.2979
-1.000 0.3902 0.02385 0.01284 -0.0923 0.8542 0.3899
-0.750 0.4271 0.02223 0.01246 -0.0929 0.8443 1.0000
-0.500 0.4613 0.02220 0.01214 -0.0935 0.8329 1.0000
-0.250 0.4907 0.02223 0.01196 -0.0934 0.8190 1.0000
0.000 0.5205 0.02219 0.01175 -0.0931 0.8045 1.0000
0.250 0.5503 0.02209 0.01150 -0.0928 0.7891 1.0000
0.500 0.5798 0.02197 0.01125 -0.0923 0.7733 1.0000
0.750 0.6090 0.02185 0.01101 -0.0918 0.7572 1.0000
1.000 0.6350 0.02186 0.01093 -0.0909 0.7391 1.0000
1.250 0.6615 0.02185 0.01084 -0.0901 0.7208 1.0000
1.500 0.6887 0.02184 0.01075 -0.0893 0.7023 1.0000
1.750 0.7164 0.02181 0.01063 -0.0886 0.6836 1.0000
2.000 0.7429 0.02186 0.01061 -0.0878 0.6637 1.0000
2.250 0.7680 0.02198 0.01066 -0.0868 0.6418 1.0000
2.500 0.7947 0.02205 0.01062 -0.0860 0.6206 1.0000
2.750 0.8184 0.02228 0.01080 -0.0849 0.5969 1.0000
3.000 0.8437 0.02247 0.01087 -0.0840 0.5748 1.0000
3.250 0.8667 0.02279 0.01113 -0.0829 0.5513 1.0000
3.500 0.8909 0.02311 0.01137 -0.0820 0.5304 1.0000
3.750 0.9143 0.02352 0.01173 -0.0811 0.5106 1.0000
4.000 0.9377 0.02397 0.01215 -0.0803 0.4926 1.0000
4.250 0.9614 0.02446 0.01261 -0.0796 0.4765 1.0000
4.500 0.9849 0.02498 0.01315 -0.0789 0.4612 1.0000
4.750 1.0079 0.02553 0.01369 -0.0781 0.4456 1.0000
5.000 1.0301 0.02610 0.01426 -0.0772 0.4296 1.0000
5.250 1.0518 0.02670 0.01490 -0.0763 0.4139 1.0000
5.500 1.0727 0.02731 0.01553 -0.0753 0.3980 1.0000
5.750 1.0930 0.02795 0.01621 -0.0742 0.3826 1.0000
6.000 1.1128 0.02860 0.01692 -0.0731 0.3678 1.0000
6.250 1.1324 0.02928 0.01768 -0.0720 0.3539 1.0000
6.500 1.1517 0.02998 0.01850 -0.0709 0.3409 1.0000
6.750 1.1708 0.03069 0.01931 -0.0697 0.3289 1.0000
7.000 1.1898 0.03143 0.02017 -0.0686 0.3177 1.0000
7.250 1.2078 0.03224 0.02116 -0.0674 0.3063 1.0000
7.500 1.2256 0.03308 0.02216 -0.0662 0.2957 1.0000
7.750 1.2432 0.03391 0.02314 -0.0649 0.2859 1.0000
8.000 1.2587 0.03485 0.02430 -0.0635 0.2748 1.0000
8.250 1.2734 0.03584 0.02547 -0.0619 0.2640 1.0000
8.500 1.2877 0.03682 0.02657 -0.0603 0.2542 1.0000
8.750 1.3005 0.03793 0.02790 -0.0587 0.2441 1.0000
9.000 1.3126 0.03911 0.02929 -0.0569 0.2351 1.0000
9.250 1.3199 0.04023 0.03049 -0.0545 0.2249 1.0000
9.500 1.3213 0.04162 0.03206 -0.0518 0.2123 1.0000
9.750 1.3209 0.04323 0.03384 -0.0494 0.1989 1.0000
10.000 1.3201 0.04504 0.03581 -0.0473 0.1854 1.0000
10.250 1.3209 0.04698 0.03802 -0.0456 0.1739 1.0000
10.500 1.3211 0.04911 0.04031 -0.0441 0.1634 1.0000
10.750 1.3191 0.05151 0.04281 -0.0429 0.1535 1.0000
11.000 1.3153 0.05425 0.04562 -0.0420 0.1444 1.0000
11.250 1.3101 0.05737 0.04881 -0.0413 0.1359 1.0000
11.500 1.3010 0.06103 0.05241 -0.0410 0.1279 1.0000
11.750 1.2917 0.06510 0.05662 -0.0411 0.1192 1.0000
12.000 1.2812 0.06947 0.06105 -0.0415 0.1120 1.0000
12.250 1.2726 0.07399 0.06583 -0.0423 0.1047 1.0000
12.500 1.2622 0.07878 0.07077 -0.0432 0.0989 1.0000
12.750 1.2528 0.08402 0.07647 -0.0446 0.0903 1.0000
13.000 1.2411 0.08986 0.08270 -0.0464 0.0806 1.0000
13.250 1.2283 0.09572 0.08867 -0.0486 0.0730 1.0000
13.500 1.2151 0.10164 0.09451 -0.0509 0.0678 1.0000
|
Polar data table (+)
Polar graphs
<< Back to I.S.A. 961 (isa961-il)