NACA 23021 (naca23021-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23021 (naca23021-il) Reynolds number: 200,000 Max Cl/Cd: 42.71 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23021-il-200000-n5.txt Download as CSV file: xf-naca23021-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 23021
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.0462 0.09710 0.09018 -0.0471 1.0000 0.0524
-19.500 -1.0425 0.09441 0.08746 -0.0480 1.0000 0.0530
-19.250 -1.0383 0.09180 0.08485 -0.0488 1.0000 0.0536
-19.000 -1.0352 0.08900 0.08202 -0.0497 1.0000 0.0543
-18.750 -1.0331 0.08604 0.07900 -0.0506 1.0000 0.0550
-18.500 -1.0310 0.08312 0.07602 -0.0515 1.0000 0.0557
-18.250 -1.0289 0.08019 0.07301 -0.0524 1.0000 0.0565
-18.000 -1.0262 0.07739 0.07011 -0.0531 1.0000 0.0572
-17.750 -1.0234 0.07459 0.06722 -0.0538 1.0000 0.0580
-17.500 -1.0192 0.07216 0.06480 -0.0542 1.0000 0.0587
-17.250 -1.0162 0.06953 0.06214 -0.0548 1.0000 0.0595
-17.000 -1.0131 0.06693 0.05951 -0.0552 1.0000 0.0603
-16.750 -1.0097 0.06436 0.05688 -0.0557 1.0000 0.0612
-16.500 -1.0058 0.06190 0.05436 -0.0560 1.0000 0.0622
-16.250 -1.0016 0.05950 0.05188 -0.0563 1.0000 0.0631
-16.000 -0.9975 0.05716 0.04949 -0.0565 1.0000 0.0640
-15.750 -0.9951 0.05467 0.04700 -0.0566 1.0000 0.0649
-15.500 -0.9921 0.05228 0.04457 -0.0568 1.0000 0.0659
-15.250 -0.9881 0.05003 0.04228 -0.0568 1.0000 0.0670
-15.000 -0.9835 0.04789 0.04008 -0.0567 1.0000 0.0683
-14.750 -0.9780 0.04589 0.03801 -0.0565 1.0000 0.0696
-14.500 -0.9750 0.04373 0.03584 -0.0562 1.0000 0.0708
-14.250 -0.9712 0.04169 0.03378 -0.0558 1.0000 0.0722
-14.000 -0.9662 0.03984 0.03190 -0.0552 1.0000 0.0737
-13.750 -0.9602 0.03814 0.03014 -0.0545 1.0000 0.0754
-13.500 -0.9547 0.03647 0.02844 -0.0537 1.0000 0.0771
-13.250 -0.9499 0.03483 0.02680 -0.0527 1.0000 0.0791
-13.000 -0.9437 0.03340 0.02533 -0.0515 1.0000 0.0814
-12.750 -0.9369 0.03210 0.02400 -0.0502 1.0000 0.0840
-12.500 -0.9326 0.03077 0.02268 -0.0485 1.0000 0.0866
-12.250 -0.9271 0.02966 0.02154 -0.0465 1.0000 0.0897
-12.000 -0.9233 0.02863 0.02049 -0.0442 1.0000 0.0927
-11.750 -0.9218 0.02766 0.01952 -0.0413 1.0000 0.0960
-11.500 -0.9192 0.02690 0.01873 -0.0382 1.0000 0.0997
-11.250 -0.9223 0.02609 0.01794 -0.0342 1.0000 0.1029
-11.000 -0.9263 0.02546 0.01730 -0.0298 1.0000 0.1064
-10.750 -0.9266 0.02489 0.01671 -0.0258 0.9993 0.1102
-10.500 -0.9022 0.02394 0.01577 -0.0267 0.9941 0.1169
-10.250 -0.8775 0.02307 0.01492 -0.0274 0.9888 0.1240
-10.000 -0.8526 0.02228 0.01415 -0.0279 0.9825 0.1321
-9.500 -0.8035 0.02073 0.01269 -0.0287 0.9694 0.1532
-9.000 -0.7577 0.01931 0.01143 -0.0282 0.9536 0.1837
-8.750 -0.7331 0.01863 0.01084 -0.0282 0.9462 0.2032
-8.500 -0.7139 0.01809 0.01039 -0.0268 0.9353 0.2219
-8.250 -0.6874 0.01756 0.00992 -0.0268 0.9274 0.2418
-8.000 -0.6672 0.01716 0.00957 -0.0254 0.9152 0.2586
-7.750 -0.6398 0.01673 0.00915 -0.0254 0.9064 0.2751
-7.500 -0.6197 0.01641 0.00886 -0.0238 0.8929 0.2886
-7.250 -0.5950 0.01607 0.00853 -0.0231 0.8825 0.3030
-7.000 -0.5719 0.01581 0.00825 -0.0220 0.8701 0.3165
-6.750 -0.5492 0.01550 0.00798 -0.0209 0.8587 0.3288
-6.500 -0.5257 0.01524 0.00771 -0.0199 0.8465 0.3412
-6.250 -0.5024 0.01501 0.00748 -0.0188 0.8343 0.3540
-6.000 -0.4784 0.01476 0.00724 -0.0179 0.8222 0.3652
-5.750 -0.4542 0.01459 0.00703 -0.0170 0.8091 0.3759
-5.500 -0.4296 0.01438 0.00681 -0.0161 0.7971 0.3857
-5.250 -0.4052 0.01424 0.00663 -0.0152 0.7837 0.3972
-5.000 -0.3814 0.01405 0.00646 -0.0142 0.7712 0.4098
-4.750 -0.3569 0.01392 0.00630 -0.0133 0.7579 0.4225
-4.500 -0.3324 0.01379 0.00617 -0.0124 0.7453 0.4352
-4.250 -0.3077 0.01367 0.00603 -0.0116 0.7325 0.4474
-4.000 -0.2828 0.01359 0.00591 -0.0107 0.7193 0.4606
-3.750 -0.2582 0.01349 0.00580 -0.0098 0.7067 0.4738
-3.500 -0.2334 0.01341 0.00572 -0.0090 0.6928 0.4862
-3.250 -0.2084 0.01335 0.00562 -0.0082 0.6786 0.4984
-3.000 -0.1834 0.01330 0.00552 -0.0074 0.6633 0.5091
-2.750 -0.1583 0.01325 0.00545 -0.0066 0.6481 0.5204
-2.500 -0.1330 0.01321 0.00538 -0.0059 0.6342 0.5311
-2.250 -0.1078 0.01318 0.00532 -0.0052 0.6199 0.5426
-2.000 -0.0823 0.01315 0.00527 -0.0045 0.6062 0.5530
-1.750 -0.0572 0.01315 0.00523 -0.0037 0.5926 0.5644
-1.500 -0.0318 0.01314 0.00520 -0.0030 0.5784 0.5753
-1.250 -0.0065 0.01314 0.00519 -0.0023 0.5650 0.5868
-1.000 0.0187 0.01316 0.00517 -0.0016 0.5513 0.5973
-0.750 0.0441 0.01317 0.00518 -0.0009 0.5379 0.6087
-0.500 0.0692 0.01321 0.00518 -0.0002 0.5249 0.6200
-0.250 0.0943 0.01324 0.00521 0.0005 0.5115 0.6323
0.000 0.1196 0.01329 0.00525 0.0012 0.4993 0.6436
0.250 0.1445 0.01335 0.00529 0.0019 0.4867 0.6555
0.500 0.1699 0.01340 0.00535 0.0026 0.4747 0.6671
1.000 0.2199 0.01356 0.00551 0.0040 0.4518 0.6927
1.250 0.2441 0.01368 0.00558 0.0048 0.4406 0.7061
1.500 0.2695 0.01376 0.00571 0.0055 0.4285 0.7184
1.750 0.2937 0.01389 0.00581 0.0063 0.4172 0.7319
2.000 0.3182 0.01401 0.00595 0.0071 0.4044 0.7461
2.250 0.3425 0.01415 0.00611 0.0080 0.3919 0.7611
2.500 0.3656 0.01433 0.00626 0.0090 0.3792 0.7773
2.750 0.3900 0.01448 0.00644 0.0098 0.3665 0.7935
3.000 0.4141 0.01468 0.00664 0.0107 0.3549 0.8074
3.250 0.4378 0.01487 0.00682 0.0116 0.3434 0.8214
3.500 0.4625 0.01509 0.00705 0.0123 0.3330 0.8337
3.750 0.4861 0.01532 0.00725 0.0132 0.3224 0.8459
4.000 0.5103 0.01556 0.00749 0.0139 0.3120 0.8581
4.250 0.5336 0.01585 0.00774 0.0148 0.3012 0.8693
4.500 0.5578 0.01611 0.00799 0.0155 0.2910 0.8808
5.000 0.6066 0.01672 0.00856 0.0167 0.2733 0.9018
5.250 0.6315 0.01708 0.00888 0.0171 0.2653 0.9110
5.500 0.6577 0.01739 0.00920 0.0173 0.2579 0.9204
5.750 0.6829 0.01775 0.00953 0.0176 0.2500 0.9294
6.000 0.7107 0.01813 0.00990 0.0173 0.2421 0.9373
6.250 0.7350 0.01850 0.01025 0.0176 0.2343 0.9464
6.500 0.7650 0.01893 0.01066 0.0168 0.2267 0.9527
6.750 0.7882 0.01932 0.01104 0.0172 0.2189 0.9621
7.000 0.8200 0.01980 0.01149 0.0158 0.2106 0.9669
7.250 0.8481 0.02027 0.01194 0.0151 0.2016 0.9736
7.500 0.8770 0.02076 0.01241 0.0141 0.1923 0.9794
7.750 0.9072 0.02130 0.01293 0.0127 0.1834 0.9846
8.000 0.9342 0.02188 0.01349 0.0119 0.1734 0.9909
8.250 0.9630 0.02255 0.01410 0.0105 0.1605 0.9955
8.500 0.9867 0.02329 0.01478 0.0099 0.1473 1.0000
8.750 0.9798 0.02379 0.01524 0.0151 0.1376 1.0000
9.000 0.9747 0.02442 0.01582 0.0198 0.1271 1.0000
9.250 0.9711 0.02520 0.01653 0.0240 0.1157 1.0000
9.500 0.9681 0.02616 0.01742 0.0278 0.1027 1.0000
9.750 0.9653 0.02733 0.01851 0.0311 0.0904 1.0000
10.000 0.9650 0.02859 0.01972 0.0338 0.0825 1.0000
10.250 0.9672 0.02991 0.02102 0.0359 0.0781 1.0000
10.500 0.9709 0.03129 0.02239 0.0376 0.0754 1.0000
10.750 0.9754 0.03274 0.02387 0.0390 0.0736 1.0000
11.000 0.9797 0.03434 0.02550 0.0401 0.0721 1.0000
11.250 0.9831 0.03611 0.02730 0.0411 0.0708 1.0000
11.500 0.9866 0.03798 0.02922 0.0418 0.0699 1.0000
11.750 0.9906 0.03991 0.03122 0.0423 0.0691 1.0000
12.000 0.9936 0.04201 0.03338 0.0427 0.0684 1.0000
12.250 0.9956 0.04430 0.03574 0.0429 0.0677 1.0000
12.500 0.9965 0.04680 0.03831 0.0429 0.0671 1.0000
12.750 0.9964 0.04949 0.04108 0.0427 0.0666 1.0000
13.000 0.9954 0.05238 0.04405 0.0424 0.0662 1.0000
13.250 0.9935 0.05547 0.04721 0.0420 0.0658 1.0000
13.500 0.9909 0.05872 0.05053 0.0414 0.0654 1.0000
13.750 0.9878 0.06210 0.05397 0.0407 0.0651 1.0000
14.000 0.9844 0.06556 0.05750 0.0399 0.0648 1.0000
14.250 0.9814 0.06903 0.06103 0.0390 0.0645 1.0000
14.500 0.9796 0.07237 0.06441 0.0382 0.0642 1.0000
14.750 0.9799 0.07551 0.06762 0.0373 0.0640 1.0000
15.000 0.9810 0.07856 0.07073 0.0365 0.0637 1.0000
15.250 0.9826 0.08155 0.07378 0.0356 0.0635 1.0000
15.500 0.9849 0.08446 0.07674 0.0348 0.0633 1.0000
15.750 0.9876 0.08731 0.07964 0.0340 0.0630 1.0000
16.000 0.9916 0.08998 0.08236 0.0332 0.0628 1.0000
16.250 0.9957 0.09265 0.08507 0.0324 0.0625 1.0000
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