TsAGI R-3a (12%) (tsagi-r-3a-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: TsAGI R-3a (12%) (tsagi-r-3a-il) Reynolds number: 50,000 Max Cl/Cd: 16.25 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tsagi-r-3a-il-50000.txt Download as CSV file: xf-tsagi-r-3a-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: TsAGI R-3a (12%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3932 0.10082 0.09486 0.0106 1.0045 0.2601
-7.500 -0.3793 0.09673 0.09084 0.0110 1.0045 0.2695
-7.250 -0.3929 0.09479 0.08906 0.0088 1.0045 0.2819
-7.000 -0.3921 0.09245 0.08682 0.0085 1.0045 0.2978
-6.750 -0.3786 0.08890 0.08336 0.0097 1.0045 0.3154
-6.500 -0.3778 0.08627 0.08085 0.0097 1.0045 0.3342
-6.000 -0.3369 0.07890 0.07365 0.0141 1.0045 0.3799
-5.750 -0.3455 0.07711 0.07204 0.0149 1.0045 0.4087
-5.500 -0.3168 0.07347 0.06848 0.0177 1.0045 0.4372
-5.250 -0.3012 0.07064 0.06578 0.0200 1.0045 0.4722
-5.000 -0.3023 0.06909 0.06444 0.0236 1.0045 0.5169
-4.500 -0.3269 0.04787 0.04158 -0.0277 0.9942 0.1578
-4.250 -0.2522 0.04114 0.03397 -0.0387 0.9653 0.1384
-4.000 -0.1824 0.03656 0.02867 -0.0474 0.9374 0.1381
-3.750 -0.1236 0.03310 0.02454 -0.0528 0.9101 0.1414
-3.500 -0.0818 0.03094 0.02221 -0.0549 0.8808 0.1499
-3.250 -0.0455 0.02919 0.02013 -0.0553 0.8564 0.1632
-3.000 -0.0168 0.02794 0.01870 -0.0545 0.8318 0.1817
-2.750 0.0107 0.02679 0.01739 -0.0531 0.8091 0.2061
-2.500 0.0382 0.02555 0.01618 -0.0515 0.7879 0.2386
-2.250 0.0638 0.02425 0.01509 -0.0498 0.7687 0.2996
-2.000 0.1512 0.02070 0.01389 -0.0522 0.7463 0.9955
-1.750 0.1723 0.02096 0.01370 -0.0511 0.7287 0.9955
-1.500 0.1936 0.02128 0.01364 -0.0501 0.7119 0.9955
-1.250 0.2152 0.02167 0.01369 -0.0491 0.6957 0.9955
-1.000 0.2374 0.02210 0.01383 -0.0482 0.6801 0.9955
-0.750 0.2596 0.02257 0.01401 -0.0472 0.6651 0.9955
-0.500 0.2818 0.02306 0.01423 -0.0460 0.6508 0.9955
-0.250 0.3039 0.02353 0.01441 -0.0446 0.6370 0.9955
0.000 0.3265 0.02417 0.01487 -0.0438 0.6216 0.9955
0.250 0.3491 0.02490 0.01543 -0.0431 0.6070 0.9955
0.500 0.3717 0.02564 0.01600 -0.0422 0.5932 0.9955
0.750 0.3947 0.02628 0.01639 -0.0409 0.5809 0.9955
1.000 0.4175 0.02712 0.01711 -0.0403 0.5670 0.9955
1.250 0.4398 0.02818 0.01810 -0.0399 0.5540 0.9955
1.500 0.4636 0.02897 0.01868 -0.0389 0.5447 0.9955
1.750 0.4853 0.03028 0.02001 -0.0389 0.5329 0.9955
2.000 0.5078 0.03143 0.02106 -0.0384 0.5235 0.9955
2.250 0.5298 0.03262 0.02221 -0.0381 0.5137 0.9955
2.500 0.5510 0.03407 0.02362 -0.0379 0.5054 0.9955
2.750 0.5710 0.03583 0.02541 -0.0381 0.4976 0.9955
3.000 0.5958 0.03667 0.02609 -0.0370 0.4919 0.9955
3.250 0.6074 0.03975 0.02939 -0.0385 0.4834 0.9955
3.500 0.6293 0.04104 0.03061 -0.0379 0.4769 0.9955
3.750 0.6449 0.04345 0.03306 -0.0382 0.4714 0.9955
4.000 0.6489 0.04748 0.03725 -0.0401 0.4655 0.9955
4.250 0.6670 0.04930 0.03906 -0.0397 0.4597 0.9955
4.500 0.6796 0.05196 0.04173 -0.0399 0.4545 0.9955
4.750 0.6644 0.05823 0.04814 -0.0432 0.4516 0.9955
5.000 0.6501 0.06390 0.05386 -0.0460 0.4501 0.9955
5.250 0.6371 0.06902 0.05899 -0.0479 0.4515 0.9955
5.500 0.6327 0.07333 0.06329 -0.0490 0.4533 0.9955
5.750 0.6397 0.07730 0.06728 -0.0502 0.4574 0.9955
6.000 0.5507 0.09212 0.08229 -0.0637 0.5820 0.9955
6.250 0.5518 0.09364 0.08378 -0.0622 0.5654 0.9955
6.500 0.5491 0.09541 0.08552 -0.0609 0.5505 0.9955
6.750 0.5546 0.09804 0.08813 -0.0604 0.5391 0.9955
7.000 0.5942 0.10231 0.09241 -0.0613 0.5281 0.9955
7.250 0.5825 0.10345 0.09352 -0.0598 0.5134 0.9955
7.500 0.5837 0.10597 0.09602 -0.0592 0.5022 0.9955
7.750 0.6127 0.10974 0.09980 -0.0597 0.4931 0.9955
8.000 0.6002 0.11148 0.10152 -0.0589 0.4824 0.9955
8.250 0.6395 0.11627 0.10635 -0.0597 0.4744 0.9955
8.500 0.6183 0.11708 0.10713 -0.0587 0.4628 0.9955
8.750 0.6606 0.12259 0.11267 -0.0595 0.4566 0.9955
9.000 0.6316 0.12279 0.11284 -0.0587 0.4466 0.9955
9.250 0.6586 0.12697 0.11704 -0.0591 0.4404 0.9955
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