I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 961 (isa961-il) Reynolds number: 200,000 Max Cl/Cd: 70.41 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa961-il-200000.txt Download as CSV file: xf-isa961-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3583 0.09275 0.08958 -0.0311 1.0000 0.0538
-8.500 -0.3782 0.09151 0.08845 -0.0303 1.0000 0.0540
-8.250 -0.3926 0.08969 0.08669 -0.0305 1.0000 0.0542
-8.000 -0.4019 0.08716 0.08419 -0.0317 1.0000 0.0544
-7.750 -0.4057 0.08417 0.08119 -0.0329 1.0000 0.0545
-7.500 -0.3999 0.07860 0.07568 -0.0318 0.9982 0.0553
-7.250 -0.3780 0.07479 0.07186 -0.0334 0.9951 0.0563
-7.000 -0.3523 0.07068 0.06771 -0.0376 0.9909 0.0576
-6.750 -0.3120 0.04452 0.04084 -0.0639 0.9840 0.0362
-6.500 -0.2853 0.03406 0.02969 -0.0701 0.9785 0.0352
-6.250 -0.2543 0.02578 0.02029 -0.0742 0.9750 0.0347
-6.000 -0.2175 0.02205 0.01575 -0.0766 0.9726 0.0355
-5.750 -0.1824 0.01974 0.01306 -0.0784 0.9693 0.0375
-5.500 -0.1481 0.01902 0.01224 -0.0797 0.9637 0.0411
-5.250 -0.1087 0.01812 0.01117 -0.0819 0.9602 0.0470
-5.000 -0.0648 0.01747 0.01042 -0.0847 0.9575 0.0570
-4.750 -0.0298 0.01744 0.01027 -0.0858 0.9487 0.0788
-4.500 0.0154 0.01678 0.00958 -0.0894 0.9451 0.0964
-4.250 0.0529 0.01673 0.00942 -0.0911 0.9388 0.1073
-4.000 0.0903 0.01678 0.00950 -0.0930 0.9335 0.1190
-3.750 0.1305 0.01616 0.00888 -0.0953 0.9300 0.1258
-3.500 0.1618 0.01573 0.00835 -0.0956 0.9216 0.1305
-3.250 0.2001 0.01508 0.00754 -0.0971 0.9156 0.1342
-3.000 0.2299 0.01438 0.00685 -0.0969 0.9044 0.1380
-2.750 0.2599 0.01388 0.00634 -0.0966 0.8925 0.1429
-2.500 0.2885 0.01353 0.00585 -0.0959 0.8792 0.1493
-2.250 0.3149 0.01301 0.00539 -0.0950 0.8649 0.1564
-2.000 0.3414 0.01263 0.00498 -0.0941 0.8511 0.1661
-1.750 0.3679 0.01222 0.00463 -0.0934 0.8388 0.1827
-1.500 0.3937 0.01186 0.00438 -0.0927 0.8260 0.2125
-1.250 0.4196 0.01156 0.00422 -0.0921 0.8131 0.2498
-1.000 0.4456 0.01126 0.00409 -0.0915 0.7998 0.3004
-0.750 0.4870 0.00935 0.00398 -0.0940 0.7863 1.0000
-0.500 0.5132 0.00938 0.00382 -0.0932 0.7709 1.0000
-0.250 0.5393 0.00942 0.00370 -0.0925 0.7545 1.0000
0.000 0.5654 0.00947 0.00361 -0.0918 0.7374 1.0000
0.250 0.5914 0.00956 0.00354 -0.0912 0.7193 1.0000
0.500 0.6169 0.00965 0.00351 -0.0904 0.6982 1.0000
0.750 0.6423 0.00978 0.00347 -0.0896 0.6753 1.0000
1.000 0.6672 0.00994 0.00347 -0.0888 0.6485 1.0000
1.250 0.6918 0.01013 0.00349 -0.0880 0.6192 1.0000
1.500 0.7160 0.01036 0.00353 -0.0871 0.5877 1.0000
1.750 0.7399 0.01063 0.00362 -0.0862 0.5558 1.0000
2.000 0.7639 0.01091 0.00373 -0.0854 0.5258 1.0000
2.250 0.7877 0.01123 0.00387 -0.0846 0.4960 1.0000
2.500 0.8112 0.01157 0.00405 -0.0838 0.4674 1.0000
2.750 0.8349 0.01192 0.00425 -0.0830 0.4421 1.0000
3.000 0.8587 0.01228 0.00448 -0.0823 0.4214 1.0000
3.250 0.8830 0.01260 0.00472 -0.0817 0.4024 1.0000
3.500 0.9071 0.01293 0.00498 -0.0811 0.3834 1.0000
3.750 0.9310 0.01327 0.00524 -0.0805 0.3650 1.0000
4.000 0.9552 0.01360 0.00551 -0.0800 0.3493 1.0000
4.250 0.9793 0.01392 0.00579 -0.0794 0.3348 1.0000
4.500 1.0034 0.01425 0.00610 -0.0789 0.3208 1.0000
4.750 1.0273 0.01459 0.00641 -0.0783 0.3077 1.0000
5.000 1.0511 0.01493 0.00674 -0.0777 0.2953 1.0000
5.250 1.0744 0.01530 0.00709 -0.0771 0.2826 1.0000
5.500 1.0975 0.01568 0.00745 -0.0764 0.2707 1.0000
5.750 1.1210 0.01604 0.00783 -0.0759 0.2605 1.0000
6.000 1.1444 0.01640 0.00823 -0.0752 0.2511 1.0000
6.250 1.1669 0.01682 0.00867 -0.0745 0.2402 1.0000
6.500 1.1888 0.01726 0.00911 -0.0737 0.2274 1.0000
6.750 1.2105 0.01771 0.00956 -0.0729 0.2124 1.0000
7.000 1.2320 0.01817 0.01002 -0.0721 0.1924 1.0000
7.250 1.2520 0.01874 0.01052 -0.0711 0.1660 1.0000
7.500 1.2695 0.01949 0.01112 -0.0698 0.1446 1.0000
7.750 1.2867 0.02027 0.01184 -0.0684 0.1341 1.0000
8.000 1.3040 0.02100 0.01260 -0.0671 0.1262 1.0000
8.250 1.3187 0.02189 0.01348 -0.0654 0.1191 1.0000
8.500 1.3367 0.02251 0.01423 -0.0641 0.1125 1.0000
8.750 1.3491 0.02345 0.01519 -0.0621 0.1059 1.0000
9.000 1.3684 0.02386 0.01575 -0.0609 0.0977 1.0000
9.250 1.3871 0.02431 0.01633 -0.0597 0.0821 1.0000
9.500 1.3956 0.02544 0.01719 -0.0574 0.0647 1.0000
9.750 1.4012 0.02678 0.01854 -0.0547 0.0576 1.0000
10.000 1.4031 0.02842 0.02027 -0.0517 0.0525 1.0000
10.250 1.4115 0.02967 0.02171 -0.0496 0.0469 1.0000
10.750 1.4244 0.03262 0.02490 -0.0456 0.0334 1.0000
11.000 1.4318 0.03409 0.02643 -0.0440 0.0280 1.0000
11.250 1.4357 0.03592 0.02827 -0.0424 0.0253 1.0000
11.500 1.4374 0.03801 0.03047 -0.0408 0.0239 1.0000
11.750 1.4370 0.04040 0.03297 -0.0394 0.0229 1.0000
12.000 1.4346 0.04311 0.03581 -0.0382 0.0221 1.0000
12.250 1.4295 0.04625 0.03909 -0.0374 0.0215 1.0000
12.500 1.4222 0.04983 0.04283 -0.0369 0.0211 1.0000
12.750 1.4128 0.05384 0.04699 -0.0368 0.0207 1.0000
13.000 1.4020 0.05823 0.05153 -0.0371 0.0205 1.0000
13.250 1.3906 0.06285 0.05629 -0.0376 0.0202 1.0000
13.500 1.3818 0.06731 0.06089 -0.0382 0.0201 1.0000
13.750 1.3734 0.07182 0.06554 -0.0391 0.0199 1.0000
14.000 1.3655 0.07636 0.07022 -0.0400 0.0196 1.0000
14.250 1.3583 0.08087 0.07486 -0.0409 0.0194 1.0000
14.500 1.3514 0.08539 0.07951 -0.0419 0.0191 1.0000
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Polar data table (+)
Polar graphs
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