NACA 23021 (naca23021-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 23021 (naca23021-il) Reynolds number: 1,000,000 Max Cl/Cd: 64.32 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca23021-il-1000000.txt Download as CSV file: xf-naca23021-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.2442 0.07495 0.07022 -0.0482 1.0000 0.0409
-19.500 -1.2453 0.07168 0.06690 -0.0491 1.0000 0.0413
-19.250 -1.2451 0.06860 0.06375 -0.0499 1.0000 0.0417
-19.000 -1.2451 0.06549 0.06057 -0.0507 1.0000 0.0421
-18.750 -1.2432 0.06265 0.05767 -0.0513 1.0000 0.0424
-18.500 -1.2401 0.06000 0.05494 -0.0518 1.0000 0.0427
-18.250 -1.2446 0.05654 0.05142 -0.0525 1.0000 0.0432
-18.000 -1.2494 0.05310 0.04793 -0.0531 1.0000 0.0437
-17.750 -1.2501 0.05015 0.04493 -0.0535 1.0000 0.0442
-17.500 -1.2480 0.04757 0.04231 -0.0537 1.0000 0.0446
-17.250 -1.2440 0.04520 0.03989 -0.0539 1.0000 0.0451
-17.000 -1.2392 0.04295 0.03759 -0.0540 1.0000 0.0456
-16.750 -1.2335 0.04084 0.03542 -0.0539 1.0000 0.0461
-16.500 -1.2263 0.03893 0.03345 -0.0538 1.0000 0.0466
-16.250 -1.2175 0.03720 0.03167 -0.0536 1.0000 0.0471
-16.000 -1.2075 0.03560 0.03002 -0.0534 1.0000 0.0475
-15.750 -1.2077 0.03319 0.02755 -0.0528 1.0000 0.0483
-15.500 -1.2030 0.03130 0.02563 -0.0522 1.0000 0.0489
-15.250 -1.1952 0.02971 0.02401 -0.0515 1.0000 0.0496
-15.000 -1.1855 0.02833 0.02259 -0.0507 1.0000 0.0502
-14.750 -1.1748 0.02709 0.02131 -0.0499 1.0000 0.0509
-14.500 -1.1632 0.02596 0.02015 -0.0490 1.0000 0.0516
-14.250 -1.1501 0.02499 0.01914 -0.0480 1.0000 0.0522
-14.000 -1.1405 0.02387 0.01798 -0.0467 1.0000 0.0530
-13.750 -1.1337 0.02267 0.01677 -0.0449 1.0000 0.0540
-13.500 -1.1254 0.02173 0.01580 -0.0429 1.0000 0.0548
-13.250 -1.1177 0.02094 0.01500 -0.0406 1.0000 0.0556
-13.000 -1.1118 0.02029 0.01432 -0.0377 1.0000 0.0564
-12.750 -1.1090 0.01976 0.01376 -0.0340 1.0000 0.0572
-12.500 -1.1115 0.01935 0.01332 -0.0293 1.0000 0.0578
-12.250 -1.0898 0.01854 0.01250 -0.0293 0.9982 0.0594
-12.000 -1.0631 0.01781 0.01178 -0.0300 0.9960 0.0611
-11.750 -1.0341 0.01721 0.01117 -0.0310 0.9939 0.0629
-11.500 -1.0048 0.01658 0.01054 -0.0321 0.9922 0.0652
-11.250 -0.9768 0.01596 0.00994 -0.0329 0.9897 0.0682
-11.000 -0.9497 0.01536 0.00937 -0.0333 0.9859 0.0722
-10.750 -0.9219 0.01477 0.00883 -0.0339 0.9818 0.0785
-10.500 -0.8939 0.01419 0.00833 -0.0345 0.9776 0.0875
-10.250 -0.8740 0.01374 0.00792 -0.0331 0.9681 0.0955
-10.000 -0.8520 0.01333 0.00752 -0.0321 0.9591 0.1024
-9.750 -0.8339 0.01296 0.00716 -0.0302 0.9471 0.1083
-9.500 -0.8160 0.01261 0.00681 -0.0283 0.9353 0.1141
-9.250 -0.7965 0.01232 0.00650 -0.0265 0.9246 0.1196
-9.000 -0.7796 0.01200 0.00620 -0.0244 0.9125 0.1263
-8.750 -0.7598 0.01173 0.00592 -0.0227 0.9016 0.1336
-8.500 -0.7392 0.01141 0.00562 -0.0213 0.8898 0.1432
-8.250 -0.7192 0.01104 0.00531 -0.0198 0.8781 0.1580
-8.000 -0.6995 0.01065 0.00498 -0.0182 0.8653 0.1791
-7.750 -0.6790 0.01026 0.00469 -0.0168 0.8532 0.2015
-7.500 -0.6573 0.00995 0.00444 -0.0155 0.8405 0.2225
-7.250 -0.6341 0.00969 0.00423 -0.0145 0.8268 0.2411
-7.000 -0.6103 0.00947 0.00405 -0.0136 0.8135 0.2577
-6.750 -0.5860 0.00930 0.00388 -0.0128 0.7997 0.2724
-6.500 -0.5603 0.00915 0.00374 -0.0122 0.7868 0.2841
-6.250 -0.5347 0.00905 0.00361 -0.0116 0.7731 0.2953
-6.000 -0.5092 0.00891 0.00348 -0.0110 0.7592 0.3058
-5.750 -0.4827 0.00883 0.00338 -0.0105 0.7468 0.3153
-5.500 -0.4571 0.00872 0.00326 -0.0099 0.7335 0.3252
-5.250 -0.4305 0.00864 0.00316 -0.0095 0.7200 0.3337
-5.000 -0.4046 0.00858 0.00306 -0.0089 0.7047 0.3427
-4.750 -0.3784 0.00849 0.00296 -0.0084 0.6899 0.3534
-4.500 -0.3520 0.00840 0.00288 -0.0079 0.6774 0.3644
-4.250 -0.3257 0.00835 0.00280 -0.0074 0.6638 0.3755
-4.000 -0.2994 0.00823 0.00272 -0.0070 0.6520 0.3892
-3.750 -0.2735 0.00817 0.00265 -0.0064 0.6386 0.4040
-3.250 -0.2205 0.00803 0.00254 -0.0055 0.6131 0.4338
-3.000 -0.1937 0.00799 0.00249 -0.0051 0.5993 0.4461
-2.750 -0.1666 0.00797 0.00246 -0.0048 0.5858 0.4582
-2.500 -0.1405 0.00794 0.00243 -0.0043 0.5714 0.4715
-2.250 -0.1129 0.00793 0.00240 -0.0041 0.5581 0.4834
-2.000 -0.0865 0.00791 0.00238 -0.0036 0.5440 0.4958
-1.500 -0.0327 0.00793 0.00236 -0.0029 0.5142 0.5180
-1.250 -0.0057 0.00797 0.00236 -0.0026 0.4986 0.5284
-1.000 0.0204 0.00800 0.00237 -0.0021 0.4826 0.5408
-0.750 0.0475 0.00803 0.00238 -0.0018 0.4685 0.5518
-0.500 0.0743 0.00805 0.00240 -0.0015 0.4560 0.5635
0.000 0.1282 0.00813 0.00244 -0.0008 0.4311 0.5848
0.250 0.1551 0.00821 0.00248 -0.0005 0.4181 0.5949
0.500 0.1818 0.00823 0.00251 -0.0002 0.4063 0.6073
0.750 0.2088 0.00830 0.00255 0.0001 0.3947 0.6181
1.000 0.2355 0.00834 0.00260 0.0004 0.3836 0.6303
1.250 0.2625 0.00840 0.00265 0.0007 0.3725 0.6414
1.500 0.2886 0.00848 0.00271 0.0011 0.3597 0.6542
1.750 0.3155 0.00852 0.00277 0.0014 0.3489 0.6670
2.000 0.3415 0.00863 0.00285 0.0019 0.3359 0.6807
2.250 0.3673 0.00872 0.00293 0.0023 0.3223 0.6939
2.750 0.4189 0.00894 0.00312 0.0032 0.2958 0.7205
3.250 0.4703 0.00918 0.00334 0.0042 0.2734 0.7485
3.500 0.4952 0.00932 0.00348 0.0048 0.2630 0.7633
3.750 0.5211 0.00943 0.00360 0.0052 0.2541 0.7773
4.000 0.5462 0.00958 0.00374 0.0058 0.2451 0.7918
4.250 0.5715 0.00970 0.00389 0.0063 0.2364 0.8068
4.500 0.5961 0.00986 0.00405 0.0069 0.2275 0.8236
4.750 0.6204 0.01003 0.00422 0.0077 0.2175 0.8400
5.000 0.6444 0.01021 0.00441 0.0084 0.2063 0.8542
5.250 0.6679 0.01046 0.00461 0.0092 0.1939 0.8661
5.500 0.6901 0.01073 0.00484 0.0102 0.1792 0.8780
5.750 0.7104 0.01112 0.00512 0.0115 0.1604 0.8887
6.000 0.7283 0.01159 0.00549 0.0132 0.1373 0.9007
6.250 0.7406 0.01224 0.00597 0.0159 0.1061 0.9125
6.500 0.7443 0.01314 0.00668 0.0200 0.0678 0.9265
6.750 0.7621 0.01354 0.00708 0.0218 0.0638 0.9372
7.000 0.7811 0.01389 0.00744 0.0233 0.0622 0.9476
7.250 0.7997 0.01427 0.00784 0.0248 0.0608 0.9583
7.500 0.8206 0.01471 0.00829 0.0258 0.0595 0.9669
7.750 0.8407 0.01516 0.00875 0.0269 0.0585 0.9762
8.000 0.8694 0.01559 0.00918 0.0261 0.0580 0.9806
8.250 0.8984 0.01606 0.00967 0.0252 0.0574 0.9848
8.500 0.9272 0.01657 0.01018 0.0243 0.0569 0.9888
8.750 0.9553 0.01711 0.01073 0.0233 0.0563 0.9918
9.000 0.9855 0.01770 0.01133 0.0219 0.0557 0.9933
9.250 1.0144 0.01834 0.01198 0.0206 0.0552 0.9953
9.500 1.0417 0.01906 0.01271 0.0194 0.0547 0.9976
9.750 1.0680 0.01987 0.01354 0.0183 0.0542 0.9997
10.000 1.0674 0.02049 0.01419 0.0223 0.0539 1.0000
10.250 1.0655 0.02119 0.01493 0.0264 0.0536 1.0000
10.500 1.0666 0.02209 0.01586 0.0296 0.0533 1.0000
10.750 1.0725 0.02304 0.01685 0.0318 0.0531 1.0000
11.000 1.0832 0.02393 0.01776 0.0333 0.0530 1.0000
11.250 1.0942 0.02491 0.01878 0.0344 0.0529 1.0000
11.500 1.1050 0.02600 0.01991 0.0354 0.0527 1.0000
11.750 1.1154 0.02720 0.02115 0.0362 0.0526 1.0000
12.000 1.1253 0.02851 0.02250 0.0370 0.0524 1.0000
12.250 1.1346 0.02993 0.02396 0.0376 0.0523 1.0000
12.500 1.1431 0.03148 0.02556 0.0381 0.0521 1.0000
12.750 1.1504 0.03318 0.02731 0.0385 0.0520 1.0000
13.000 1.1570 0.03501 0.02919 0.0388 0.0519 1.0000
13.250 1.1629 0.03698 0.03122 0.0390 0.0517 1.0000
13.500 1.1678 0.03909 0.03338 0.0390 0.0516 1.0000
13.750 1.1719 0.04134 0.03569 0.0390 0.0515 1.0000
14.000 1.1753 0.04372 0.03813 0.0389 0.0513 1.0000
14.250 1.1779 0.04625 0.04071 0.0387 0.0512 1.0000
14.500 1.1798 0.04891 0.04343 0.0383 0.0510 1.0000
14.750 1.1807 0.05171 0.04629 0.0379 0.0509 1.0000
15.000 1.1811 0.05462 0.04927 0.0374 0.0508 1.0000
15.250 1.1812 0.05760 0.05230 0.0368 0.0506 1.0000
15.500 1.1809 0.06066 0.05542 0.0362 0.0505 1.0000
15.750 1.1796 0.06386 0.05869 0.0354 0.0504 1.0000
16.000 1.1785 0.06709 0.06197 0.0347 0.0503 1.0000
16.250 1.1784 0.07019 0.06513 0.0339 0.0503 1.0000
16.500 1.1772 0.07347 0.06847 0.0330 0.0502 1.0000
16.750 1.1771 0.07660 0.07165 0.0322 0.0501 1.0000
17.000 1.1769 0.07977 0.07486 0.0313 0.0500 1.0000
17.250 1.1777 0.08281 0.07795 0.0304 0.0499 1.0000
17.500 1.1783 0.08593 0.08111 0.0295 0.0498 1.0000
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