I.S.A. 961 (isa961-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: I.S.A. 961 (isa961-il) Reynolds number: 500,000 Max Cl/Cd: 80.02 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-isa961-il-500000.txt Download as CSV file: xf-isa961-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2629 0.08618 0.08420 -0.0325 1.0000 0.0252
-9.500 -0.2737 0.08437 0.08245 -0.0301 0.9998 0.0259
-9.250 -0.2744 0.07790 0.07599 -0.0370 0.9973 0.0282
-9.000 -0.3494 0.08678 0.08470 -0.0313 1.0000 0.0246
-8.750 -0.2700 0.06566 0.06377 -0.0453 0.9911 0.0291
-8.250 -0.3697 0.03030 0.02731 -0.0852 0.9787 0.0163
-8.000 -0.3454 0.02269 0.01874 -0.0895 0.9745 0.0158
-7.750 -0.3134 0.01969 0.01523 -0.0916 0.9726 0.0160
-7.500 -0.2810 0.01780 0.01298 -0.0931 0.9701 0.0164
-7.250 -0.2522 0.01651 0.01144 -0.0934 0.9647 0.0168
-7.000 -0.2197 0.01553 0.01024 -0.0944 0.9612 0.0171
-6.750 -0.1883 0.01376 0.00823 -0.0953 0.9581 0.0179
-6.500 -0.1606 0.01289 0.00729 -0.0953 0.9517 0.0190
-6.250 -0.1299 0.01226 0.00658 -0.0957 0.9459 0.0205
-6.000 -0.1012 0.01167 0.00588 -0.0956 0.9373 0.0217
-5.750 -0.0728 0.01099 0.00507 -0.0953 0.9275 0.0231
-5.500 -0.0462 0.01047 0.00446 -0.0946 0.9159 0.0258
-5.250 -0.0197 0.01008 0.00398 -0.0939 0.9048 0.0296
-5.000 0.0075 0.00978 0.00382 -0.0935 0.8957 0.0557
-4.750 0.0359 0.01006 0.00403 -0.0932 0.8865 0.0678
-4.500 0.0628 0.01001 0.00397 -0.0928 0.8754 0.0740
-4.250 0.0901 0.01006 0.00391 -0.0924 0.8637 0.0784
-4.000 0.1167 0.00977 0.00356 -0.0919 0.8528 0.0836
-3.750 0.1438 0.00960 0.00335 -0.0916 0.8418 0.0873
-3.500 0.1711 0.00949 0.00319 -0.0912 0.8299 0.0913
-3.250 0.1981 0.00929 0.00292 -0.0908 0.8172 0.0955
-3.000 0.2249 0.00910 0.00270 -0.0904 0.8020 0.0995
-2.750 0.2520 0.00897 0.00250 -0.0900 0.7862 0.1022
-2.500 0.2792 0.00887 0.00232 -0.0897 0.7711 0.1048
-2.250 0.3065 0.00877 0.00216 -0.0894 0.7562 0.1079
-2.000 0.3337 0.00869 0.00206 -0.0890 0.7404 0.1139
-1.750 0.3610 0.00866 0.00197 -0.0887 0.7237 0.1215
-1.500 0.3880 0.00863 0.00191 -0.0884 0.7062 0.1363
-1.250 0.4150 0.00860 0.00188 -0.0881 0.6875 0.1595
-1.000 0.4418 0.00861 0.00184 -0.0878 0.6652 0.1794
-0.750 0.4679 0.00865 0.00182 -0.0874 0.6368 0.1983
-0.500 0.4936 0.00873 0.00183 -0.0869 0.6036 0.2209
-0.250 0.5190 0.00881 0.00186 -0.0864 0.5677 0.2601
0.000 0.5437 0.00880 0.00193 -0.0859 0.5275 0.3521
0.250 0.5789 0.00753 0.00209 -0.0878 0.4864 1.0000
0.500 0.6037 0.00783 0.00217 -0.0872 0.4529 1.0000
0.750 0.6288 0.00810 0.00226 -0.0867 0.4246 1.0000
1.000 0.6541 0.00835 0.00236 -0.0862 0.3995 1.0000
1.250 0.6794 0.00862 0.00247 -0.0858 0.3741 1.0000
1.500 0.7045 0.00892 0.00259 -0.0853 0.3447 1.0000
1.750 0.7297 0.00920 0.00272 -0.0849 0.3179 1.0000
2.000 0.7549 0.00950 0.00287 -0.0844 0.2920 1.0000
2.250 0.7798 0.00982 0.00303 -0.0840 0.2676 1.0000
2.500 0.8048 0.01013 0.00321 -0.0835 0.2464 1.0000
2.750 0.8298 0.01043 0.00340 -0.0831 0.2286 1.0000
3.000 0.8550 0.01072 0.00359 -0.0827 0.2109 1.0000
3.250 0.8802 0.01100 0.00377 -0.0824 0.1939 1.0000
3.500 0.9023 0.01162 0.00410 -0.0816 0.1402 1.0000
3.750 0.9264 0.01201 0.00438 -0.0811 0.1280 1.0000
4.000 0.9513 0.01231 0.00465 -0.0806 0.1222 1.0000
4.250 0.9767 0.01256 0.00489 -0.0803 0.1184 1.0000
4.500 1.0021 0.01279 0.00514 -0.0800 0.1160 1.0000
4.750 1.0272 0.01304 0.00540 -0.0796 0.1137 1.0000
5.000 1.0521 0.01331 0.00568 -0.0792 0.1114 1.0000
5.250 1.0766 0.01362 0.00600 -0.0788 0.1086 1.0000
5.500 1.1012 0.01390 0.00629 -0.0784 0.1047 1.0000
5.750 1.1264 0.01411 0.00653 -0.0781 0.1016 1.0000
6.000 1.1507 0.01441 0.00683 -0.0776 0.0968 1.0000
6.250 1.1746 0.01473 0.00716 -0.0771 0.0915 1.0000
6.500 1.1980 0.01508 0.00745 -0.0766 0.0699 1.0000
6.750 1.2192 0.01564 0.00789 -0.0758 0.0614 1.0000
7.000 1.2411 0.01611 0.00839 -0.0750 0.0589 1.0000
7.250 1.2619 0.01666 0.00898 -0.0740 0.0561 1.0000
7.500 1.2825 0.01721 0.00956 -0.0731 0.0527 1.0000
7.750 1.3040 0.01764 0.01006 -0.0723 0.0504 1.0000
8.000 1.3253 0.01806 0.01055 -0.0715 0.0471 1.0000
8.250 1.3436 0.01872 0.01125 -0.0702 0.0425 1.0000
8.500 1.3669 0.01892 0.01147 -0.0697 0.0368 1.0000
8.750 1.3816 0.01980 0.01215 -0.0680 0.0187 1.0000
9.000 1.3961 0.02064 0.01301 -0.0660 0.0157 1.0000
9.250 1.4097 0.02137 0.01385 -0.0639 0.0149 1.0000
9.500 1.4212 0.02222 0.01481 -0.0616 0.0141 1.0000
9.750 1.4309 0.02320 0.01593 -0.0591 0.0134 1.0000
10.000 1.4385 0.02437 0.01720 -0.0565 0.0129 1.0000
10.250 1.4429 0.02578 0.01874 -0.0537 0.0123 1.0000
10.500 1.4422 0.02763 0.02074 -0.0507 0.0118 1.0000
10.750 1.4482 0.02906 0.02227 -0.0486 0.0115 1.0000
11.000 1.4538 0.03059 0.02391 -0.0468 0.0112 1.0000
11.250 1.4567 0.03241 0.02584 -0.0450 0.0109 1.0000
11.500 1.4577 0.03450 0.02805 -0.0433 0.0106 1.0000
11.750 1.4570 0.03687 0.03053 -0.0418 0.0104 1.0000
12.000 1.4552 0.03948 0.03328 -0.0406 0.0102 1.0000
12.250 1.4518 0.04241 0.03633 -0.0397 0.0100 1.0000
12.500 1.4474 0.04562 0.03965 -0.0391 0.0099 1.0000
12.750 1.4417 0.04911 0.04325 -0.0388 0.0097 1.0000
13.000 1.4351 0.05288 0.04714 -0.0388 0.0096 1.0000
13.250 1.4279 0.05688 0.05126 -0.0391 0.0095 1.0000
13.500 1.4196 0.06113 0.05561 -0.0396 0.0094 1.0000
13.750 1.4111 0.06557 0.06016 -0.0403 0.0093 1.0000
14.000 1.4023 0.07012 0.06481 -0.0410 0.0091 1.0000
14.250 1.3940 0.07462 0.06941 -0.0418 0.0091 1.0000
14.500 1.3862 0.07906 0.07393 -0.0425 0.0090 1.0000
14.750 1.3793 0.08326 0.07821 -0.0430 0.0089 1.0000
15.000 1.3738 0.08699 0.08201 -0.0429 0.0087 1.0000
15.250 1.3706 0.09016 0.08524 -0.0421 0.0086 1.0000
15.500 1.3654 0.09463 0.08984 -0.0434 0.0086 1.0000
15.750 1.3596 0.09946 0.09481 -0.0453 0.0085 1.0000
16.000 1.3529 0.10457 0.10006 -0.0476 0.0084 1.0000
16.250 1.3465 0.10966 0.10528 -0.0498 0.0084 1.0000
16.500 1.3397 0.11490 0.11068 -0.0522 0.0083 1.0000
16.750 1.3332 0.12009 0.11599 -0.0545 0.0082 1.0000
17.000 1.3265 0.12541 0.12144 -0.0571 0.0081 1.0000
17.250 1.3195 0.13079 0.12696 -0.0597 0.0080 1.0000
17.500 1.3124 0.13630 0.13259 -0.0625 0.0080 1.0000
17.750 1.3053 0.14190 0.13832 -0.0654 0.0079 1.0000
18.000 1.2976 0.14778 0.14432 -0.0686 0.0079 1.0000
18.250 1.2899 0.15379 0.15047 -0.0720 0.0079 1.0000
18.500 1.2816 0.16009 0.15690 -0.0758 0.0079 1.0000
18.750 1.2728 0.16664 0.16358 -0.0797 0.0079 1.0000
19.000 1.2634 0.17355 0.17062 -0.0841 0.0079 1.0000
19.250 1.2535 0.18085 0.17806 -0.0887 0.0079 1.0000
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Polar data table (+)
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