NACA 23021 (naca23021-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 23021 (naca23021-il) Reynolds number: 100,000 Max Cl/Cd: 35.68 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca23021-il-100000-n5.txt Download as CSV file: xf-naca23021-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.250 -0.8719 0.11812 0.11073 -0.0405 1.0000 0.0692
-19.000 -0.9300 0.10450 0.09665 -0.0485 1.0000 0.0699
-18.750 -0.9181 0.10305 0.09526 -0.0487 1.0000 0.0707
-18.500 -0.9196 0.09940 0.09156 -0.0502 1.0000 0.0716
-18.250 -0.9259 0.09503 0.08709 -0.0521 1.0000 0.0725
-18.000 -0.9338 0.09050 0.08241 -0.0540 1.0000 0.0735
-17.750 -0.9422 0.08596 0.07771 -0.0558 1.0000 0.0746
-17.500 -0.9507 0.08152 0.07306 -0.0574 1.0000 0.0757
-17.250 -0.9531 0.07805 0.06946 -0.0584 1.0000 0.0768
-17.000 -0.9462 0.07596 0.06740 -0.0587 1.0000 0.0780
-16.750 -0.9425 0.07343 0.06483 -0.0591 1.0000 0.0792
-16.500 -0.9406 0.07067 0.06199 -0.0597 1.0000 0.0805
-16.250 -0.9389 0.06791 0.05911 -0.0601 1.0000 0.0820
-16.000 -0.9379 0.06510 0.05612 -0.0604 1.0000 0.0836
-15.750 -0.9302 0.06324 0.05431 -0.0603 1.0000 0.0850
-15.500 -0.9244 0.06118 0.05224 -0.0603 1.0000 0.0866
-15.250 -0.9196 0.05900 0.04999 -0.0603 1.0000 0.0885
-15.000 -0.9148 0.05684 0.04772 -0.0601 1.0000 0.0906
-14.750 -0.9083 0.05493 0.04579 -0.0598 1.0000 0.0925
-14.500 -0.9019 0.05311 0.04397 -0.0594 1.0000 0.0945
-14.250 -0.8964 0.05120 0.04203 -0.0590 1.0000 0.0969
-14.000 -0.8903 0.04936 0.04008 -0.0585 1.0000 0.0998
-13.750 -0.8847 0.04761 0.03838 -0.0578 1.0000 0.1021
-13.500 -0.8796 0.04584 0.03660 -0.0571 1.0000 0.1050
-13.250 -0.8738 0.04416 0.03485 -0.0563 1.0000 0.1085
-13.000 -0.8698 0.04246 0.03317 -0.0552 1.0000 0.1116
-12.750 -0.8664 0.04078 0.03150 -0.0540 1.0000 0.1152
-12.500 -0.8615 0.03927 0.02991 -0.0527 1.0000 0.1196
-12.250 -0.8610 0.03763 0.02834 -0.0510 1.0000 0.1233
-12.000 -0.8590 0.03620 0.02690 -0.0491 1.0000 0.1280
-11.750 -0.8585 0.03484 0.02555 -0.0467 1.0000 0.1327
-11.500 -0.8603 0.03355 0.02430 -0.0439 1.0000 0.1376
-11.250 -0.8615 0.03246 0.02321 -0.0408 1.0000 0.1432
-11.000 -0.8668 0.03139 0.02219 -0.0370 1.0000 0.1486
-10.500 -0.8801 0.02972 0.02058 -0.0280 1.0000 0.1604
-10.250 -0.8888 0.02910 0.01996 -0.0228 1.0000 0.1671
-10.000 -0.9030 0.02854 0.01946 -0.0165 1.0000 0.1728
-9.750 -0.9175 0.02812 0.01906 -0.0099 1.0000 0.1794
-9.500 -0.9070 0.02738 0.01839 -0.0080 0.9952 0.1924
-9.250 -0.8813 0.02657 0.01764 -0.0088 0.9882 0.2112
-9.000 -0.8551 0.02581 0.01699 -0.0096 0.9803 0.2308
-8.750 -0.8287 0.02517 0.01642 -0.0102 0.9723 0.2512
-8.500 -0.7994 0.02461 0.01589 -0.0111 0.9646 0.2714
-8.250 -0.7717 0.02411 0.01542 -0.0116 0.9562 0.2895
-8.000 -0.7414 0.02364 0.01497 -0.0125 0.9484 0.3076
-7.750 -0.7122 0.02321 0.01457 -0.0131 0.9405 0.3261
-7.500 -0.6838 0.02280 0.01420 -0.0134 0.9315 0.3436
-7.250 -0.6513 0.02240 0.01380 -0.0144 0.9245 0.3603
-7.000 -0.6265 0.02207 0.01347 -0.0138 0.9132 0.3738
-6.750 -0.5908 0.02166 0.01310 -0.0152 0.9068 0.3865
-6.500 -0.5684 0.02138 0.01276 -0.0140 0.8940 0.3980
-6.250 -0.5342 0.02101 0.01244 -0.0150 0.8866 0.4096
-6.000 -0.5116 0.02077 0.01217 -0.0138 0.8739 0.4206
-5.750 -0.4801 0.02045 0.01185 -0.0142 0.8656 0.4342
-5.500 -0.4577 0.02025 0.01170 -0.0129 0.8530 0.4474
-5.250 -0.4285 0.01997 0.01141 -0.0128 0.8439 0.4631
-5.000 -0.4056 0.01980 0.01125 -0.0116 0.8311 0.4766
-4.750 -0.3755 0.01953 0.01100 -0.0115 0.8216 0.4891
-4.500 -0.3523 0.01936 0.01078 -0.0104 0.8085 0.5015
-4.250 -0.3212 0.01910 0.01054 -0.0105 0.7986 0.5121
-4.000 -0.2982 0.01895 0.01034 -0.0093 0.7849 0.5242
-3.750 -0.2674 0.01874 0.01014 -0.0094 0.7746 0.5348
-3.500 -0.2443 0.01861 0.00995 -0.0082 0.7605 0.5474
-3.250 -0.2151 0.01845 0.00984 -0.0080 0.7489 0.5580
-3.000 -0.1901 0.01832 0.00964 -0.0071 0.7355 0.5705
-2.750 -0.1626 0.01823 0.00958 -0.0066 0.7222 0.5813
-2.500 -0.1360 0.01811 0.00938 -0.0059 0.7093 0.5939
-2.250 -0.1101 0.01806 0.00936 -0.0052 0.6941 0.6048
-2.000 -0.0840 0.01797 0.00920 -0.0044 0.6803 0.6171
-1.750 -0.0572 0.01793 0.00917 -0.0038 0.6653 0.6284
-1.500 -0.0324 0.01790 0.00911 -0.0029 0.6506 0.6408
-1.250 -0.0049 0.01789 0.00906 -0.0024 0.6372 0.6525
-1.000 0.0200 0.01789 0.00904 -0.0015 0.6224 0.6645
-0.750 0.0464 0.01792 0.00906 -0.0009 0.6087 0.6764
-0.500 0.0728 0.01794 0.00903 -0.0002 0.5952 0.6886
-0.250 0.0980 0.01800 0.00910 0.0006 0.5808 0.7014
0.000 0.1249 0.01807 0.00914 0.0011 0.5678 0.7131
0.250 0.1497 0.01814 0.00918 0.0020 0.5540 0.7265
0.500 0.1772 0.01827 0.00932 0.0025 0.5406 0.7379
0.750 0.2015 0.01837 0.00933 0.0034 0.5285 0.7523
1.000 0.2297 0.01856 0.00957 0.0037 0.5145 0.7639
1.250 0.2552 0.01872 0.00967 0.0045 0.5025 0.7778
1.500 0.2819 0.01892 0.00988 0.0051 0.4896 0.7910
1.750 0.3092 0.01915 0.01009 0.0055 0.4774 0.8036
2.000 0.3332 0.01935 0.01023 0.0065 0.4658 0.8178
2.250 0.3633 0.01964 0.01053 0.0063 0.4535 0.8277
2.500 0.3858 0.01984 0.01065 0.0075 0.4428 0.8417
2.750 0.4179 0.02018 0.01100 0.0069 0.4304 0.8499
3.000 0.4401 0.02040 0.01113 0.0081 0.4207 0.8636
3.250 0.4733 0.02076 0.01152 0.0072 0.4082 0.8708
3.500 0.4981 0.02105 0.01170 0.0079 0.3981 0.8826
3.750 0.5288 0.02138 0.01206 0.0073 0.3853 0.8908
4.000 0.5570 0.02171 0.01233 0.0072 0.3741 0.9005
4.250 0.5845 0.02203 0.01261 0.0071 0.3620 0.9098
4.500 0.6160 0.02239 0.01296 0.0063 0.3501 0.9178
4.750 0.6414 0.02273 0.01321 0.0065 0.3396 0.9279
5.000 0.6763 0.02312 0.01361 0.0048 0.3279 0.9343
5.500 0.7390 0.02388 0.01431 0.0026 0.3077 0.9498
5.750 0.7694 0.02430 0.01465 0.0016 0.2992 0.9580
6.000 0.8023 0.02470 0.01510 0.0001 0.2902 0.9650
6.250 0.8345 0.02515 0.01547 -0.0015 0.2821 0.9722
6.500 0.8663 0.02558 0.01596 -0.0029 0.2729 0.9795
6.750 0.8989 0.02606 0.01637 -0.0047 0.2647 0.9862
7.000 0.9316 0.02653 0.01691 -0.0065 0.2564 0.9929
7.250 0.9643 0.02703 0.01738 -0.0084 0.2487 0.9990
7.500 0.9714 0.02738 0.01776 -0.0054 0.2432 1.0000
7.750 0.9711 0.02769 0.01811 -0.0010 0.2380 1.0000
8.000 0.9652 0.02800 0.01841 0.0043 0.2338 1.0000
8.250 0.9583 0.02834 0.01871 0.0098 0.2301 1.0000
8.500 0.9568 0.02873 0.01917 0.0142 0.2255 1.0000
8.750 0.9551 0.02920 0.01967 0.0185 0.2205 1.0000
9.000 0.9531 0.02977 0.02021 0.0226 0.2155 1.0000
9.250 0.9543 0.03042 0.02090 0.0260 0.2093 1.0000
9.500 0.9547 0.03118 0.02168 0.0293 0.2029 1.0000
9.750 0.9565 0.03206 0.02256 0.0321 0.1967 1.0000
10.000 0.9598 0.03303 0.02358 0.0344 0.1900 1.0000
10.250 0.9622 0.03418 0.02473 0.0366 0.1837 1.0000
10.500 0.9656 0.03544 0.02605 0.0383 0.1761 1.0000
10.750 0.9675 0.03691 0.02754 0.0399 0.1687 1.0000
11.000 0.9679 0.03864 0.02928 0.0413 0.1606 1.0000
11.250 0.9683 0.04053 0.03122 0.0423 0.1518 1.0000
11.500 0.9665 0.04275 0.03346 0.0432 0.1432 1.0000
11.750 0.9624 0.04532 0.03605 0.0438 0.1348 1.0000
12.000 0.9568 0.04821 0.03895 0.0441 0.1268 1.0000
12.250 0.9506 0.05135 0.04213 0.0441 0.1195 1.0000
12.500 0.9423 0.05487 0.04568 0.0438 0.1137 1.0000
12.750 0.9329 0.05870 0.04955 0.0433 0.1087 1.0000
13.000 0.9233 0.06272 0.05362 0.0425 0.1048 1.0000
13.250 0.9139 0.06687 0.05782 0.0416 0.1013 1.0000
13.500 0.9036 0.07125 0.06223 0.0405 0.0987 1.0000
13.750 0.8970 0.07525 0.06631 0.0395 0.0963 1.0000
14.000 0.8906 0.07929 0.07041 0.0384 0.0942 1.0000
14.250 0.8847 0.08333 0.07449 0.0372 0.0925 1.0000
14.500 0.8801 0.08720 0.07838 0.0360 0.0911 1.0000
14.750 0.8784 0.09070 0.08191 0.0350 0.0897 1.0000
15.000 0.8780 0.09406 0.08533 0.0340 0.0885 1.0000
15.250 0.8786 0.09731 0.08863 0.0330 0.0873 1.0000
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