TSAGI 12% AIRFOIL (tsagi12-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: TSAGI 12% AIRFOIL (tsagi12-il) Reynolds number: 50,000 Max Cl/Cd: 32.27 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tsagi12-il-50000-n5.txt Download as CSV file: xf-tsagi12-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5015 0.10109 0.09403 -0.0311 1.0000 0.0546
-10.500 -0.5065 0.09578 0.08879 -0.0336 1.0000 0.0544
-10.250 -0.5139 0.09001 0.08307 -0.0368 1.0000 0.0541
-10.000 -0.5235 0.08403 0.07714 -0.0406 1.0000 0.0537
-9.750 -0.5391 0.07846 0.07160 -0.0432 1.0000 0.0534
-9.500 -0.5574 0.07383 0.06696 -0.0439 1.0000 0.0531
-9.250 -0.5775 0.06994 0.06304 -0.0426 1.0000 0.0528
-9.000 -0.5968 0.06627 0.05929 -0.0402 1.0000 0.0528
-8.750 -0.6141 0.06249 0.05535 -0.0376 1.0000 0.0530
-8.500 -0.6279 0.05884 0.05148 -0.0344 1.0000 0.0535
-8.250 -0.6398 0.05530 0.04762 -0.0308 1.0000 0.0543
-8.000 -0.6499 0.05191 0.04379 -0.0267 1.0000 0.0552
-7.750 -0.6449 0.04974 0.04165 -0.0242 1.0000 0.0572
-7.500 -0.6406 0.04761 0.03939 -0.0213 1.0000 0.0591
-7.250 -0.6386 0.04505 0.03653 -0.0179 1.0000 0.0605
-7.000 -0.6356 0.04261 0.03371 -0.0143 1.0000 0.0627
-6.750 -0.6325 0.04034 0.03095 -0.0105 1.0000 0.0659
-6.500 -0.6262 0.03829 0.02859 -0.0072 1.0000 0.0691
-6.250 -0.6162 0.03666 0.02684 -0.0046 1.0000 0.0720
-6.000 -0.6057 0.03506 0.02499 -0.0019 1.0000 0.0757
-5.750 -0.5953 0.03365 0.02307 0.0011 1.0000 0.0809
-5.500 -0.5818 0.03224 0.02170 0.0031 1.0000 0.0854
-5.250 -0.5660 0.03094 0.02021 0.0050 1.0000 0.0898
-5.000 -0.5379 0.02959 0.01861 0.0045 0.9960 0.0976
-4.750 -0.4970 0.02833 0.01715 0.0018 0.9877 0.1093
-4.500 -0.4547 0.02712 0.01584 -0.0012 0.9797 0.1217
-4.250 -0.4131 0.02617 0.01492 -0.0043 0.9710 0.1421
-4.000 -0.3710 0.02527 0.01399 -0.0075 0.9623 0.1703
-3.750 -0.3338 0.02432 0.01320 -0.0099 0.9516 0.2127
-3.500 -0.2989 0.02312 0.01240 -0.0120 0.9409 0.2802
-3.250 -0.2705 0.02154 0.01175 -0.0127 0.9303 0.4374
-3.000 -0.1532 0.02157 0.01296 -0.0248 0.9379 0.8543
-2.750 -0.0748 0.02253 0.01351 -0.0322 0.9346 0.9354
-2.500 0.0134 0.02254 0.01308 -0.0434 0.9309 0.9739
-2.250 0.0988 0.02185 0.01204 -0.0552 0.9249 1.0000
-2.000 0.1380 0.02157 0.01154 -0.0582 0.9084 1.0000
-1.750 0.1745 0.02133 0.01109 -0.0605 0.8919 1.0000
-1.500 0.2081 0.02114 0.01072 -0.0620 0.8754 1.0000
-1.250 0.2386 0.02100 0.01041 -0.0629 0.8593 1.0000
-1.000 0.2653 0.02093 0.01019 -0.0630 0.8429 1.0000
-0.750 0.2898 0.02091 0.01005 -0.0626 0.8267 1.0000
-0.500 0.3130 0.02093 0.00994 -0.0619 0.8112 1.0000
-0.250 0.3354 0.02097 0.00988 -0.0610 0.7962 1.0000
0.000 0.3573 0.02103 0.00985 -0.0600 0.7819 1.0000
0.250 0.3791 0.02110 0.00984 -0.0589 0.7680 1.0000
0.500 0.4002 0.02120 0.00987 -0.0577 0.7541 1.0000
0.750 0.4207 0.02134 0.00996 -0.0564 0.7404 1.0000
1.000 0.4411 0.02149 0.01007 -0.0551 0.7269 1.0000
1.250 0.4616 0.02165 0.01021 -0.0538 0.7137 1.0000
1.500 0.4826 0.02182 0.01036 -0.0527 0.7013 1.0000
1.750 0.5045 0.02198 0.01051 -0.0516 0.6894 1.0000
2.000 0.5270 0.02212 0.01063 -0.0505 0.6782 1.0000
2.250 0.5474 0.02238 0.01092 -0.0493 0.6657 1.0000
2.500 0.5679 0.02264 0.01121 -0.0481 0.6537 1.0000
2.750 0.5890 0.02290 0.01150 -0.0469 0.6427 1.0000
3.000 0.6115 0.02309 0.01171 -0.0458 0.6329 1.0000
3.250 0.6308 0.02346 0.01215 -0.0445 0.6211 1.0000
3.500 0.6506 0.02382 0.01258 -0.0432 0.6102 1.0000
3.750 0.6721 0.02410 0.01292 -0.0420 0.6005 1.0000
4.000 0.6919 0.02446 0.01337 -0.0406 0.5900 1.0000
4.250 0.7106 0.02491 0.01393 -0.0392 0.5792 1.0000
4.500 0.7313 0.02523 0.01436 -0.0378 0.5697 1.0000
4.750 0.7511 0.02561 0.01484 -0.0364 0.5596 1.0000
5.000 0.7688 0.02612 0.01549 -0.0348 0.5489 1.0000
5.250 0.7887 0.02649 0.01597 -0.0333 0.5391 1.0000
5.500 0.8088 0.02684 0.01648 -0.0319 0.5293 1.0000
5.750 0.8254 0.02739 0.01720 -0.0301 0.5181 1.0000
6.000 0.8438 0.02783 0.01779 -0.0284 0.5077 1.0000
6.250 0.8658 0.02805 0.01812 -0.0270 0.4979 1.0000
6.500 0.8815 0.02861 0.01888 -0.0250 0.4860 1.0000
6.750 0.8978 0.02913 0.01963 -0.0230 0.4741 1.0000
7.000 0.9151 0.02951 0.02018 -0.0210 0.4613 1.0000
7.250 0.9318 0.02971 0.02053 -0.0187 0.4456 1.0000
7.500 0.9480 0.02981 0.02075 -0.0162 0.4279 1.0000
7.750 0.9641 0.02988 0.02092 -0.0137 0.4094 1.0000
8.000 0.9711 0.03026 0.02147 -0.0101 0.3868 1.0000
8.250 0.9747 0.03046 0.02177 -0.0059 0.3577 1.0000
8.500 0.9731 0.03087 0.02217 -0.0012 0.3229 1.0000
8.750 0.9696 0.03159 0.02285 0.0034 0.2855 1.0000
9.000 0.9636 0.03263 0.02370 0.0080 0.2443 1.0000
9.250 0.9515 0.03402 0.02482 0.0132 0.2054 1.0000
9.500 0.9367 0.03592 0.02644 0.0178 0.1692 1.0000
9.750 0.9214 0.03836 0.02862 0.0214 0.1395 1.0000
10.000 0.9075 0.04116 0.03121 0.0240 0.1184 1.0000
10.250 0.8952 0.04419 0.03409 0.0260 0.1024 1.0000
10.500 0.8846 0.04732 0.03709 0.0274 0.0913 1.0000
10.750 0.8764 0.05041 0.04012 0.0286 0.0827 1.0000
11.000 0.8716 0.05331 0.04304 0.0297 0.0753 1.0000
11.250 0.8677 0.05619 0.04590 0.0306 0.0696 1.0000
11.500 0.8675 0.05880 0.04859 0.0315 0.0640 1.0000
11.750 0.8678 0.06142 0.05126 0.0323 0.0590 1.0000
12.000 0.8693 0.06386 0.05366 0.0331 0.0560 1.0000
12.250 0.8777 0.06588 0.05596 0.0345 0.0528 1.0000
12.500 0.8840 0.06816 0.05841 0.0354 0.0498 1.0000
12.750 0.8880 0.07065 0.06096 0.0360 0.0469 1.0000
13.000 0.8956 0.07286 0.06315 0.0370 0.0448 1.0000
13.250 0.8984 0.07609 0.06673 0.0373 0.0431 1.0000
13.500 0.8994 0.07961 0.07053 0.0374 0.0422 1.0000
13.750 0.8947 0.08387 0.07505 0.0368 0.0414 1.0000
14.000 0.8864 0.08861 0.08003 0.0356 0.0409 1.0000
14.250 0.8745 0.09407 0.08571 0.0337 0.0408 1.0000
14.500 0.8587 0.10041 0.09226 0.0310 0.0407 1.0000
14.750 0.8401 0.10770 0.09974 0.0275 0.0410 1.0000
15.000 0.8181 0.11628 0.10849 0.0231 0.0414 1.0000
15.250 0.7944 0.12603 0.11836 0.0179 0.0421 1.0000
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