NACA 2410 (naca2410-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2410 (naca2410-il) Reynolds number: 200,000 Max Cl/Cd: 67.27 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2410-il-200000.txt Download as CSV file: xf-naca2410-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2410
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3936 0.11300 0.10942 -0.0212 1.0000 0.0626
-11.000 -0.3908 0.10977 0.10620 -0.0218 1.0000 0.0651
-10.750 -0.5323 0.11221 0.10849 -0.0161 1.0000 0.0601
-10.500 -0.5207 0.10975 0.10602 -0.0149 1.0000 0.0616
-10.250 -0.5144 0.10664 0.10291 -0.0154 1.0000 0.0635
-10.000 -0.4153 0.09108 0.08760 -0.0291 1.0000 0.0730
-9.750 -0.4053 0.08850 0.08503 -0.0280 1.0000 0.0750
-9.500 -0.4044 0.08480 0.08134 -0.0286 1.0000 0.0772
-9.250 -0.4099 0.08027 0.07683 -0.0302 1.0000 0.0798
-9.000 -0.6155 0.05953 0.05580 -0.0500 1.0000 0.0466
-8.750 -0.6276 0.05395 0.05008 -0.0505 1.0000 0.0457
-8.500 -0.6408 0.04803 0.04387 -0.0499 1.0000 0.0450
-8.250 -0.6495 0.04243 0.03787 -0.0484 1.0000 0.0450
-8.000 -0.6516 0.03762 0.03256 -0.0463 1.0000 0.0454
-7.750 -0.6474 0.03363 0.02804 -0.0441 1.0000 0.0461
-7.500 -0.6367 0.03108 0.02496 -0.0419 1.0000 0.0473
-7.250 -0.6259 0.02760 0.02116 -0.0404 1.0000 0.0495
-7.000 -0.6080 0.02652 0.02005 -0.0391 1.0000 0.0518
-6.750 -0.5898 0.02503 0.01832 -0.0377 1.0000 0.0541
-6.500 -0.5707 0.02382 0.01679 -0.0362 1.0000 0.0569
-6.250 -0.5509 0.02243 0.01507 -0.0349 1.0000 0.0593
-6.000 -0.5302 0.02077 0.01335 -0.0341 1.0000 0.0620
-5.750 -0.5089 0.02010 0.01261 -0.0331 1.0000 0.0653
-5.500 -0.4867 0.01934 0.01169 -0.0321 1.0000 0.0682
-5.250 -0.4640 0.01871 0.01088 -0.0312 1.0000 0.0705
-5.000 -0.4408 0.01748 0.00963 -0.0307 1.0000 0.0741
-4.750 -0.4175 0.01688 0.00903 -0.0300 1.0000 0.0774
-4.500 -0.3935 0.01634 0.00842 -0.0294 1.0000 0.0810
-4.250 -0.3694 0.01583 0.00784 -0.0289 1.0000 0.0852
-4.000 -0.3456 0.01525 0.00735 -0.0286 1.0000 0.0916
-3.750 -0.3072 0.01462 0.00675 -0.0309 0.9966 0.1021
-3.500 -0.2664 0.01403 0.00625 -0.0339 0.9925 0.1262
-3.250 -0.2262 0.01339 0.00589 -0.0368 0.9877 0.1752
-3.000 -0.1855 0.01293 0.00570 -0.0399 0.9829 0.2355
-2.750 -0.1461 0.01250 0.00553 -0.0427 0.9768 0.2996
-2.500 -0.1068 0.01206 0.00539 -0.0453 0.9711 0.3740
-2.250 -0.0695 0.01143 0.00529 -0.0476 0.9648 0.4935
-2.000 -0.0338 0.01076 0.00529 -0.0490 0.9593 0.6532
-1.750 -0.0021 0.01032 0.00529 -0.0490 0.9518 0.7741
-1.500 0.0370 0.01009 0.00529 -0.0500 0.9481 0.8762
-1.250 0.0814 0.01004 0.00525 -0.0525 0.9416 0.9461
-1.000 0.1439 0.00994 0.00509 -0.0592 0.9391 0.9857
-0.750 0.2034 0.00976 0.00482 -0.0657 0.9353 1.0000
-0.500 0.2357 0.00959 0.00458 -0.0664 0.9227 1.0000
-0.250 0.2659 0.00943 0.00435 -0.0666 0.9095 1.0000
0.000 0.2938 0.00929 0.00415 -0.0663 0.8952 1.0000
0.250 0.3200 0.00918 0.00397 -0.0656 0.8797 1.0000
0.500 0.3453 0.00910 0.00382 -0.0647 0.8633 1.0000
0.750 0.3704 0.00904 0.00370 -0.0637 0.8461 1.0000
1.000 0.3954 0.00902 0.00359 -0.0627 0.8285 1.0000
1.250 0.4200 0.00904 0.00353 -0.0616 0.8096 1.0000
1.500 0.4445 0.00909 0.00350 -0.0606 0.7893 1.0000
1.750 0.4693 0.00916 0.00348 -0.0597 0.7693 1.0000
2.000 0.4941 0.00926 0.00349 -0.0587 0.7492 1.0000
2.250 0.5187 0.00938 0.00354 -0.0578 0.7276 1.0000
2.500 0.5436 0.00952 0.00358 -0.0569 0.7071 1.0000
2.750 0.5684 0.00968 0.00367 -0.0561 0.6862 1.0000
3.000 0.5932 0.00985 0.00377 -0.0552 0.6646 1.0000
3.250 0.6180 0.01005 0.00386 -0.0544 0.6433 1.0000
3.500 0.6423 0.01023 0.00400 -0.0535 0.6187 1.0000
3.750 0.6668 0.01044 0.00412 -0.0526 0.5952 1.0000
4.000 0.6911 0.01066 0.00427 -0.0517 0.5702 1.0000
4.250 0.7151 0.01089 0.00444 -0.0508 0.5430 1.0000
4.500 0.7387 0.01115 0.00460 -0.0499 0.5135 1.0000
4.750 0.7623 0.01142 0.00479 -0.0489 0.4837 1.0000
5.000 0.7860 0.01171 0.00502 -0.0481 0.4540 1.0000
5.250 0.8092 0.01203 0.00526 -0.0472 0.4204 1.0000
5.500 0.8318 0.01242 0.00553 -0.0462 0.3825 1.0000
5.750 0.8537 0.01290 0.00586 -0.0451 0.3375 1.0000
6.000 0.8740 0.01355 0.00628 -0.0439 0.2798 1.0000
6.250 0.8916 0.01455 0.00688 -0.0425 0.2040 1.0000
6.500 0.9062 0.01601 0.00782 -0.0407 0.1264 1.0000
6.750 0.9231 0.01725 0.00883 -0.0390 0.0965 1.0000
7.000 0.9421 0.01822 0.00977 -0.0377 0.0849 1.0000
7.250 0.9591 0.01941 0.01087 -0.0361 0.0781 1.0000
7.500 0.9803 0.02018 0.01175 -0.0349 0.0741 1.0000
7.750 1.0006 0.02105 0.01264 -0.0338 0.0701 1.0000
8.000 1.0186 0.02240 0.01393 -0.0324 0.0662 1.0000
8.250 1.0399 0.02343 0.01506 -0.0314 0.0638 1.0000
8.500 1.0613 0.02435 0.01610 -0.0304 0.0609 1.0000
8.750 1.0820 0.02532 0.01711 -0.0294 0.0578 1.0000
9.000 1.1028 0.02701 0.01876 -0.0287 0.0549 1.0000
9.250 1.1235 0.02844 0.02038 -0.0277 0.0525 1.0000
9.500 1.1436 0.02960 0.02173 -0.0266 0.0499 1.0000
9.750 1.1626 0.03083 0.02308 -0.0255 0.0473 1.0000
10.000 1.1818 0.03268 0.02490 -0.0248 0.0446 1.0000
10.250 1.1973 0.03514 0.02766 -0.0234 0.0427 1.0000
10.500 1.2111 0.03687 0.02970 -0.0216 0.0409 1.0000
10.750 1.2238 0.03857 0.03162 -0.0199 0.0388 1.0000
11.000 1.2361 0.04000 0.03316 -0.0183 0.0370 1.0000
11.250 1.2478 0.04266 0.03588 -0.0172 0.0354 1.0000
11.500 1.2451 0.04728 0.04089 -0.0146 0.0345 1.0000
11.750 1.2394 0.04942 0.04337 -0.0111 0.0340 1.0000
12.000 1.2283 0.05198 0.04625 -0.0075 0.0335 1.0000
12.250 1.2140 0.05501 0.04958 -0.0045 0.0332 1.0000
12.500 1.1974 0.05852 0.05338 -0.0024 0.0329 1.0000
12.750 1.1785 0.06262 0.05774 -0.0014 0.0326 1.0000
13.000 1.1572 0.06742 0.06279 -0.0015 0.0326 1.0000
13.250 1.1338 0.07304 0.06865 -0.0030 0.0326 1.0000
13.500 1.1081 0.07966 0.07548 -0.0058 0.0328 1.0000
13.750 1.0810 0.08726 0.08327 -0.0099 0.0332 1.0000
14.000 1.0529 0.09590 0.09207 -0.0150 0.0337 1.0000
14.250 1.0245 0.10545 0.10173 -0.0206 0.0342 1.0000
14.500 0.6680 0.14879 0.14542 -0.0292 0.0778 1.0000
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