NACA 23021 (naca23021-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23021 (naca23021-il) Reynolds number: 50,000 Max Cl/Cd: 24.8 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23021-il-50000-n5.txt Download as CSV file: xf-naca23021-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.7483 0.09471 0.08494 -0.0521 1.0000 0.1191
-15.500 -0.7589 0.08966 0.07983 -0.0538 1.0000 0.1213
-15.250 -0.7566 0.08672 0.07687 -0.0543 1.0000 0.1239
-15.000 -0.7807 0.08007 0.07001 -0.0567 1.0000 0.1265
-14.750 -0.8059 0.07371 0.06337 -0.0587 1.0000 0.1291
-14.500 -0.8101 0.07021 0.05976 -0.0591 1.0000 0.1319
-14.250 -0.8003 0.06853 0.05814 -0.0586 1.0000 0.1354
-14.000 -0.8044 0.06524 0.05472 -0.0587 1.0000 0.1393
-13.750 -0.8081 0.06209 0.05143 -0.0586 1.0000 0.1433
-13.500 -0.7974 0.06066 0.05011 -0.0578 1.0000 0.1478
-13.250 -0.7989 0.05794 0.04726 -0.0574 1.0000 0.1528
-13.000 -0.7929 0.05613 0.04551 -0.0566 1.0000 0.1579
-12.750 -0.7904 0.05409 0.04346 -0.0557 1.0000 0.1639
-12.500 -0.7881 0.05210 0.04148 -0.0546 1.0000 0.1702
-12.250 -0.7851 0.05034 0.03975 -0.0534 1.0000 0.1771
-12.000 -0.7837 0.04852 0.03796 -0.0519 1.0000 0.1843
-11.750 -0.7831 0.04683 0.03630 -0.0502 1.0000 0.1925
-11.500 -0.7823 0.04532 0.03486 -0.0482 1.0000 0.2007
-11.250 -0.7851 0.04369 0.03320 -0.0459 1.0000 0.2101
-11.000 -0.7853 0.04252 0.03219 -0.0432 1.0000 0.2189
-10.750 -0.7902 0.04118 0.03086 -0.0399 1.0000 0.2290
-10.500 -0.7949 0.04016 0.02992 -0.0363 1.0000 0.2389
-10.250 -0.8015 0.03920 0.02904 -0.0322 1.0000 0.2489
-10.000 -0.8130 0.03826 0.02808 -0.0272 1.0000 0.2596
-9.750 -0.8225 0.03767 0.02761 -0.0219 1.0000 0.2692
-9.500 -0.8386 0.03694 0.02685 -0.0157 1.0000 0.2797
-9.250 -0.8460 0.03645 0.02646 -0.0105 1.0000 0.2909
-9.000 -0.8534 0.03591 0.02596 -0.0054 1.0000 0.3029
-8.750 -0.8617 0.03530 0.02531 -0.0001 1.0000 0.3160
-8.500 -0.8616 0.03500 0.02513 0.0041 1.0000 0.3287
-8.250 -0.8628 0.03458 0.02474 0.0084 1.0000 0.3418
-8.000 -0.8637 0.03414 0.02426 0.0126 1.0000 0.3554
-7.750 -0.8500 0.03395 0.02416 0.0146 0.9978 0.3690
-7.500 -0.8153 0.03370 0.02389 0.0127 0.9893 0.3861
-7.250 -0.7816 0.03341 0.02355 0.0110 0.9799 0.4024
-7.000 -0.7510 0.03303 0.02307 0.0097 0.9698 0.4184
-6.750 -0.7108 0.03299 0.02306 0.0074 0.9616 0.4335
-6.500 -0.6799 0.03284 0.02293 0.0066 0.9504 0.4478
-6.250 -0.6472 0.03267 0.02273 0.0055 0.9403 0.4646
-6.000 -0.6162 0.03245 0.02246 0.0047 0.9295 0.4823
-5.750 -0.5826 0.03250 0.02256 0.0040 0.9186 0.4973
-5.500 -0.5430 0.03237 0.02244 0.0020 0.9093 0.5113
-5.250 -0.5194 0.03190 0.02186 0.0023 0.8966 0.5253
-5.000 -0.4719 0.03188 0.02189 -0.0006 0.8886 0.5366
-4.750 -0.4471 0.03150 0.02145 -0.0002 0.8759 0.5496
-4.500 -0.4037 0.03135 0.02132 -0.0025 0.8672 0.5614
-4.250 -0.3784 0.03108 0.02102 -0.0019 0.8545 0.5738
-4.000 -0.3393 0.03084 0.02077 -0.0034 0.8452 0.5864
-3.750 -0.3126 0.03068 0.02060 -0.0029 0.8321 0.5981
-3.500 -0.2770 0.03035 0.02023 -0.0038 0.8226 0.6118
-3.250 -0.2485 0.03031 0.02022 -0.0034 0.8092 0.6226
-3.000 -0.2160 0.02987 0.01970 -0.0038 0.7995 0.6373
-2.750 -0.1850 0.02999 0.01987 -0.0037 0.7856 0.6472
-2.500 -0.1514 0.02955 0.01936 -0.0041 0.7762 0.6617
-2.250 -0.1220 0.02970 0.01955 -0.0037 0.7612 0.6717
-2.000 -0.0913 0.02939 0.01918 -0.0036 0.7504 0.6856
-1.750 -0.0588 0.02946 0.01927 -0.0035 0.7361 0.6962
-1.500 -0.0330 0.02931 0.01908 -0.0027 0.7228 0.7094
-1.250 0.0050 0.02927 0.01901 -0.0034 0.7101 0.7205
-1.000 0.0281 0.02927 0.01899 -0.0021 0.6948 0.7332
-0.750 0.0655 0.02921 0.01887 -0.0028 0.6823 0.7445
-0.250 0.1203 0.02937 0.01898 -0.0014 0.6523 0.7692
0.000 0.1569 0.02934 0.01886 -0.0020 0.6396 0.7803
0.250 0.1786 0.02953 0.01905 -0.0007 0.6240 0.7941
0.500 0.2150 0.02971 0.01919 -0.0015 0.6099 0.8040
0.750 0.2385 0.02970 0.01910 -0.0003 0.5968 0.8189
1.000 0.2767 0.03005 0.01944 -0.0017 0.5812 0.8272
1.250 0.3011 0.03003 0.01933 -0.0007 0.5693 0.8418
1.500 0.3414 0.03033 0.01961 -0.0025 0.5537 0.8495
1.750 0.3620 0.03049 0.01974 -0.0013 0.5407 0.8640
2.000 0.4082 0.03063 0.01975 -0.0041 0.5274 0.8708
2.250 0.4271 0.03089 0.02005 -0.0028 0.5135 0.8852
2.500 0.4724 0.03115 0.02024 -0.0059 0.4995 0.8918
2.750 0.5031 0.03130 0.02032 -0.0065 0.4871 0.9037
3.000 0.5392 0.03164 0.02067 -0.0084 0.4733 0.9124
3.250 0.5739 0.03175 0.02062 -0.0096 0.4627 0.9232
3.500 0.6074 0.03218 0.02113 -0.0114 0.4489 0.9326
3.750 0.6387 0.03241 0.02126 -0.0123 0.4387 0.9438
4.000 0.6762 0.03280 0.02170 -0.0147 0.4262 0.9522
4.250 0.7092 0.03312 0.02196 -0.0162 0.4162 0.9626
4.500 0.7458 0.03352 0.02240 -0.0186 0.4049 0.9713
4.750 0.7825 0.03387 0.02271 -0.0209 0.3956 0.9803
5.000 0.8169 0.03439 0.02330 -0.0232 0.3851 0.9895
5.250 0.8565 0.03466 0.02349 -0.0260 0.3762 0.9972
5.500 0.8696 0.03529 0.02424 -0.0246 0.3673 1.0000
5.750 0.8813 0.03553 0.02440 -0.0223 0.3605 1.0000
6.000 0.8861 0.03608 0.02499 -0.0192 0.3534 1.0000
6.250 0.8885 0.03666 0.02562 -0.0157 0.3460 1.0000
6.500 0.9011 0.03683 0.02566 -0.0133 0.3394 1.0000
6.750 0.8982 0.03761 0.02654 -0.0091 0.3326 1.0000
7.000 0.8982 0.03820 0.02716 -0.0052 0.3257 1.0000
7.250 0.9123 0.03829 0.02709 -0.0030 0.3193 1.0000
7.500 0.9008 0.03934 0.02828 0.0024 0.3131 1.0000
7.750 0.8975 0.04005 0.02902 0.0067 0.3069 1.0000
8.000 0.9112 0.04018 0.02901 0.0089 0.3010 1.0000
8.250 0.8959 0.04135 0.03028 0.0146 0.2956 1.0000
8.500 0.8815 0.04241 0.03140 0.0200 0.2904 1.0000
8.750 0.8866 0.04288 0.03181 0.0231 0.2848 1.0000
9.000 0.8856 0.04375 0.03267 0.0265 0.2796 1.0000
9.250 0.8646 0.04576 0.03481 0.0312 0.2741 1.0000
9.500 0.8669 0.04670 0.03573 0.0337 0.2679 1.0000
9.750 0.8727 0.04759 0.03658 0.0357 0.2620 1.0000
10.000 0.8456 0.05097 0.04014 0.0387 0.2561 1.0000
10.250 0.8542 0.05175 0.04089 0.0401 0.2494 1.0000
10.500 0.8396 0.05472 0.04394 0.0416 0.2429 1.0000
10.750 0.8164 0.05890 0.04826 0.0424 0.2358 1.0000
11.000 0.8368 0.05869 0.04793 0.0434 0.2292 1.0000
11.250 0.7746 0.06825 0.05781 0.0421 0.2210 1.0000
11.500 0.8065 0.06658 0.05603 0.0434 0.2154 1.0000
11.750 0.7279 0.07998 0.06974 0.0395 0.2047 1.0000
12.000 0.7673 0.07691 0.06657 0.0414 0.2003 1.0000
12.250 0.7085 0.08863 0.07848 0.0375 0.1884 1.0000
12.750 0.7105 0.09413 0.08401 0.0365 0.1731 1.0000
13.000 0.6838 0.10172 0.09165 0.0339 0.1618 1.0000
13.500 0.6901 0.10707 0.09697 0.0326 0.1484 1.0000
14.000 0.6803 0.11584 0.10571 0.0298 0.1363 1.0000
14.250 0.6396 0.12799 0.11790 0.0249 0.1279 1.0000
14.500 0.6553 0.12863 0.11851 0.0250 0.1263 1.0000
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