TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: TSAGI 12% AIRFOIL (tsagi12-il) Reynolds number: 100,000 Max Cl/Cd: 49.59 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tsagi12-il-100000.txt Download as CSV file: xf-tsagi12-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: TSAGI 12% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4630 0.10460 0.09958 -0.0223 1.0000 0.1229
-10.000 -0.4758 0.10087 0.09594 -0.0257 1.0000 0.1282
-9.750 -0.5191 0.09595 0.09118 -0.0346 1.0000 0.1298
-9.500 -0.4741 0.09291 0.08804 -0.0268 1.0000 0.1348
-9.250 -0.4766 0.08942 0.08460 -0.0279 1.0000 0.1400
-9.000 -0.5223 0.08452 0.07984 -0.0346 1.0000 0.1436
-8.750 -0.5756 0.08242 0.07773 -0.0331 1.0000 0.1444
-8.500 -0.5102 0.07724 0.07262 -0.0320 1.0000 0.1519
-8.250 -0.5377 0.07436 0.06978 -0.0305 1.0000 0.1561
-8.000 -0.6068 0.07392 0.06909 -0.0266 1.0000 0.1594
-7.750 -0.5547 0.06795 0.06341 -0.0268 1.0000 0.1658
-7.500 -0.6100 0.06809 0.06322 -0.0215 1.0000 0.1743
-7.250 -0.6359 0.04991 0.04411 -0.0181 1.0000 0.0857
-7.000 -0.6384 0.04645 0.04053 -0.0141 1.0000 0.0824
-6.750 -0.6470 0.04327 0.03704 -0.0088 1.0000 0.0803
-6.500 -0.6521 0.04084 0.03433 -0.0039 1.0000 0.0801
-6.250 -0.6557 0.03839 0.03154 0.0010 1.0000 0.0795
-6.000 -0.6562 0.03603 0.02882 0.0055 1.0000 0.0793
-5.750 -0.6531 0.03384 0.02624 0.0095 1.0000 0.0790
-5.500 -0.6461 0.03203 0.02411 0.0128 1.0000 0.0802
-5.250 -0.6371 0.03069 0.02245 0.0158 1.0000 0.0833
-5.000 -0.5982 0.02890 0.01995 0.0139 0.9925 0.0877
-4.750 -0.5562 0.02656 0.01757 0.0105 0.9853 0.0949
-4.500 -0.5118 0.02500 0.01564 0.0075 0.9768 0.1026
-4.250 -0.4621 0.02365 0.01421 0.0031 0.9697 0.1157
-4.000 -0.4202 0.02229 0.01291 0.0003 0.9599 0.1304
-3.750 -0.3769 0.02111 0.01193 -0.0030 0.9517 0.1568
-3.500 -0.3367 0.01997 0.01104 -0.0056 0.9428 0.1936
-3.250 -0.3034 0.01883 0.01036 -0.0070 0.9329 0.2590
-3.000 -0.1734 0.01786 0.01208 -0.0214 0.9468 0.9028
-2.750 -0.0798 0.01887 0.01268 -0.0320 0.9470 0.9441
-2.500 0.0359 0.01886 0.01233 -0.0479 0.9510 0.9781
-2.250 0.1306 0.01796 0.01118 -0.0614 0.9494 1.0000
-2.000 0.1808 0.01745 0.01050 -0.0665 0.9364 1.0000
-1.750 0.2258 0.01700 0.00991 -0.0705 0.9209 1.0000
-1.500 0.2644 0.01666 0.00944 -0.0731 0.9036 1.0000
-1.250 0.2967 0.01643 0.00909 -0.0743 0.8855 1.0000
-1.000 0.3243 0.01629 0.00883 -0.0744 0.8676 1.0000
-0.750 0.3478 0.01623 0.00866 -0.0737 0.8504 1.0000
-0.500 0.3690 0.01623 0.00855 -0.0725 0.8339 1.0000
-0.250 0.3886 0.01627 0.00850 -0.0709 0.8174 1.0000
0.000 0.4078 0.01634 0.00849 -0.0693 0.8013 1.0000
0.250 0.4272 0.01641 0.00850 -0.0678 0.7859 1.0000
0.500 0.4468 0.01650 0.00851 -0.0662 0.7709 1.0000
0.750 0.4667 0.01659 0.00853 -0.0646 0.7564 1.0000
1.000 0.4869 0.01669 0.00856 -0.0631 0.7425 1.0000
1.250 0.5069 0.01681 0.00866 -0.0617 0.7283 1.0000
1.500 0.5270 0.01695 0.00876 -0.0602 0.7143 1.0000
1.750 0.5474 0.01711 0.00890 -0.0589 0.7009 1.0000
2.000 0.5680 0.01728 0.00905 -0.0575 0.6881 1.0000
2.250 0.5889 0.01745 0.00921 -0.0562 0.6761 1.0000
2.500 0.6109 0.01760 0.00931 -0.0550 0.6653 1.0000
2.750 0.6318 0.01779 0.00952 -0.0538 0.6534 1.0000
3.000 0.6524 0.01804 0.00982 -0.0525 0.6417 1.0000
3.250 0.6737 0.01827 0.01007 -0.0513 0.6311 1.0000
3.500 0.6965 0.01842 0.01019 -0.0502 0.6216 1.0000
3.750 0.7164 0.01872 0.01058 -0.0489 0.6100 1.0000
4.000 0.7373 0.01900 0.01094 -0.0477 0.5995 1.0000
4.250 0.7605 0.01916 0.01107 -0.0466 0.5906 1.0000
4.500 0.7801 0.01948 0.01151 -0.0452 0.5792 1.0000
4.750 0.8004 0.01980 0.01192 -0.0439 0.5687 1.0000
5.000 0.8231 0.01998 0.01214 -0.0427 0.5595 1.0000
5.250 0.8433 0.02028 0.01255 -0.0413 0.5486 1.0000
5.500 0.8629 0.02059 0.01298 -0.0398 0.5372 1.0000
5.750 0.8836 0.02077 0.01323 -0.0383 0.5254 1.0000
6.000 0.9045 0.02080 0.01333 -0.0367 0.5118 1.0000
6.250 0.9247 0.02081 0.01339 -0.0349 0.4969 1.0000
6.500 0.9440 0.02074 0.01336 -0.0329 0.4794 1.0000
6.750 0.9637 0.02039 0.01292 -0.0306 0.4576 1.0000
7.000 0.9778 0.02028 0.01288 -0.0278 0.4324 1.0000
7.250 0.9926 0.02026 0.01289 -0.0251 0.4083 1.0000
7.500 1.0060 0.02034 0.01302 -0.0222 0.3829 1.0000
7.750 1.0156 0.02048 0.01328 -0.0188 0.3493 1.0000
8.000 1.0186 0.02086 0.01358 -0.0143 0.2857 1.0000
8.250 1.0003 0.02292 0.01472 -0.0073 0.1661 1.0000
8.500 0.9821 0.02538 0.01655 -0.0006 0.1129 1.0000
8.750 0.9718 0.02719 0.01822 0.0051 0.0951 1.0000
9.000 0.9627 0.02866 0.01961 0.0105 0.0874 1.0000
9.250 0.9559 0.02998 0.02095 0.0157 0.0799 1.0000
9.500 0.9504 0.03151 0.02238 0.0200 0.0746 1.0000
9.750 0.9546 0.03291 0.02383 0.0231 0.0695 1.0000
10.000 0.9635 0.03437 0.02526 0.0256 0.0651 1.0000
10.250 0.9896 0.03641 0.02716 0.0261 0.0607 1.0000
10.500 1.0065 0.03793 0.02886 0.0277 0.0574 1.0000
10.750 1.0235 0.03966 0.03069 0.0289 0.0541 1.0000
11.000 1.0660 0.04282 0.03387 0.0267 0.0516 1.0000
11.250 1.0992 0.04723 0.03850 0.0251 0.0505 1.0000
11.500 1.0979 0.04930 0.04090 0.0286 0.0500 1.0000
11.750 1.0935 0.05143 0.04330 0.0323 0.0496 1.0000
12.000 1.0833 0.05348 0.04562 0.0363 0.0491 1.0000
12.250 1.0719 0.05581 0.04822 0.0396 0.0486 1.0000
12.500 1.0584 0.05851 0.05118 0.0423 0.0482 1.0000
12.750 1.0461 0.06175 0.05466 0.0443 0.0483 1.0000
13.000 1.0313 0.06526 0.05840 0.0456 0.0485 1.0000
13.250 1.0148 0.06915 0.06251 0.0464 0.0488 1.0000
13.500 0.9973 0.07338 0.06693 0.0465 0.0491 1.0000
13.750 0.9781 0.07817 0.07190 0.0460 0.0495 1.0000
14.000 0.9582 0.08334 0.07723 0.0448 0.0498 1.0000
14.250 0.9400 0.08891 0.08293 0.0433 0.0502 1.0000
14.500 0.9257 0.09451 0.08866 0.0417 0.0508 1.0000
14.750 0.8911 0.10130 0.09567 0.0372 0.0514 1.0000
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Polar data table (+)
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