NACA 16-021 (naca16021-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 16-021 (naca16021-il) Reynolds number: 100,000 Max Cl/Cd: 20.69 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca16021-il-100000-n5.txt Download as CSV file: xf-naca16021-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 16-021
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
------ -------- --------- --------- -------- -------- --------
-18.000 -0.8290 0.12003 0.11405 -0.0687 1.0000 0.0455
-17.750 -0.8798 0.10923 0.10298 -0.0722 1.0000 0.0452
-17.500 -0.9176 0.10161 0.09510 -0.0734 1.0000 0.0452
-17.250 -0.9492 0.09550 0.08875 -0.0733 1.0000 0.0454
-17.000 -0.9769 0.09031 0.08331 -0.0724 1.0000 0.0457
-16.750 -1.0018 0.08578 0.07852 -0.0708 1.0000 0.0460
-16.500 -1.0242 0.08176 0.07423 -0.0687 1.0000 0.0464
-16.250 -1.0452 0.07810 0.07029 -0.0661 1.0000 0.0468
-16.000 -1.0645 0.07480 0.06669 -0.0631 1.0000 0.0473
-15.750 -1.0644 0.07302 0.06491 -0.0613 1.0000 0.0480
-15.500 -1.0673 0.07120 0.06300 -0.0590 1.0000 0.0486
-15.250 -1.0688 0.06918 0.06088 -0.0572 0.9996 0.0493
-15.000 -1.0650 0.06698 0.05850 -0.0564 0.9982 0.0502
-14.750 -1.0603 0.06484 0.05617 -0.0555 0.9967 0.0512
-14.500 -1.0550 0.06279 0.05389 -0.0546 0.9953 0.0524
-14.250 -1.0487 0.06085 0.05168 -0.0535 0.9940 0.0537
-14.000 -1.0403 0.05910 0.04967 -0.0524 0.9928 0.0550
-13.750 -1.0259 0.05782 0.04839 -0.0518 0.9915 0.0561
-13.500 -1.0131 0.05656 0.04707 -0.0510 0.9900 0.0573
-13.250 -0.9992 0.05531 0.04572 -0.0503 0.9884 0.0587
-13.000 -0.9841 0.05409 0.04436 -0.0498 0.9868 0.0606
-12.750 -0.9671 0.05295 0.04300 -0.0495 0.9853 0.0625
-12.500 -0.9482 0.05189 0.04188 -0.0494 0.9841 0.0643
-12.250 -0.9311 0.05093 0.04090 -0.0491 0.9830 0.0661
-12.000 -0.9178 0.04997 0.03988 -0.0478 0.9812 0.0680
-11.750 -0.9039 0.04905 0.03888 -0.0466 0.9793 0.0703
-11.500 -0.8877 0.04821 0.03788 -0.0457 0.9774 0.0731
-11.250 -0.8735 0.04720 0.03691 -0.0448 0.9755 0.0757
-11.000 -0.8574 0.04632 0.03599 -0.0442 0.9738 0.0789
-10.750 -0.8397 0.04552 0.03509 -0.0437 0.9724 0.0827
-10.500 -0.8246 0.04462 0.03418 -0.0429 0.9713 0.0865
-10.250 -0.8182 0.04379 0.03334 -0.0401 0.9685 0.0905
-10.000 -0.8061 0.04306 0.03252 -0.0383 0.9660 0.0961
-9.750 -0.7950 0.04214 0.03166 -0.0366 0.9636 0.1020
-9.500 -0.7792 0.04142 0.03087 -0.0356 0.9616 0.1100
-9.250 -0.7651 0.04060 0.03010 -0.0345 0.9600 0.1191
-9.000 -0.7494 0.03989 0.02941 -0.0335 0.9587 0.1308
-8.750 -0.7456 0.03923 0.02877 -0.0299 0.9552 0.1419
-8.500 -0.7361 0.03852 0.02812 -0.0275 0.9522 0.1573
-8.250 -0.7239 0.03777 0.02748 -0.0257 0.9496 0.1782
-8.000 -0.7105 0.03703 0.02688 -0.0241 0.9476 0.2061
-7.750 -0.6982 0.03622 0.02630 -0.0224 0.9460 0.2441
-7.250 -0.6962 0.03450 0.02515 -0.0141 0.9392 0.3405
-7.000 -0.6936 0.03355 0.02468 -0.0101 0.9361 0.4160
-6.750 -0.6665 0.03364 0.02554 -0.0097 0.9349 0.5331
-6.500 -0.5962 0.03643 0.02874 -0.0154 0.9350 0.6228
-6.250 -0.5643 0.03741 0.02968 -0.0156 0.9334 0.6545
-6.000 -0.5387 0.03791 0.03010 -0.0152 0.9318 0.6774
-5.750 -0.5169 0.03836 0.03044 -0.0141 0.9295 0.6955
-5.500 -0.5136 0.03857 0.03060 -0.0093 0.9244 0.7108
-5.250 -0.5000 0.03888 0.03082 -0.0067 0.9215 0.7260
-5.000 -0.4718 0.03974 0.03158 -0.0065 0.9194 0.7378
-4.750 -0.4334 0.04098 0.03272 -0.0080 0.9179 0.7484
-4.500 -0.4015 0.04185 0.03349 -0.0086 0.9164 0.7614
-4.250 -0.3955 0.04225 0.03384 -0.0044 0.9122 0.7747
-4.000 -0.3580 0.04331 0.03482 -0.0060 0.9098 0.7792
-3.750 -0.3490 0.04330 0.03474 -0.0029 0.9062 0.7908
-3.500 -0.3087 0.04384 0.03519 -0.0057 0.9044 0.7938
-3.250 -0.2744 0.04410 0.03537 -0.0075 0.9027 0.7982
-3.000 -0.2588 0.04385 0.03504 -0.0060 0.9009 0.8074
-2.750 -0.2370 0.04429 0.03544 -0.0053 0.8968 0.8104
-2.500 -0.2166 0.04446 0.03558 -0.0044 0.8927 0.8153
-2.250 -0.2063 0.04422 0.03528 -0.0018 0.8894 0.8235
-2.000 -0.1705 0.04442 0.03543 -0.0041 0.8877 0.8258
-1.750 -0.1361 0.04450 0.03546 -0.0062 0.8862 0.8291
-1.500 -0.1457 0.04435 0.03529 0.0005 0.8799 0.8386
-1.250 -0.1160 0.04459 0.03551 -0.0006 0.8767 0.8407
-1.000 -0.0844 0.04468 0.03558 -0.0021 0.8741 0.8434
-0.750 -0.0548 0.04465 0.03552 -0.0033 0.8719 0.8472
-0.500 -0.0409 0.04428 0.03512 -0.0014 0.8697 0.8544
-0.250 -0.0280 0.04469 0.03555 0.0008 0.8629 0.8568
0.000 0.0000 0.04475 0.03561 0.0000 0.8594 0.8594
0.250 0.0279 0.04468 0.03555 -0.0008 0.8568 0.8629
0.500 0.0409 0.04428 0.03512 0.0014 0.8544 0.8697
0.750 0.0549 0.04464 0.03552 0.0033 0.8472 0.8719
1.000 0.0844 0.04468 0.03558 0.0021 0.8434 0.8741
1.250 0.1159 0.04458 0.03551 0.0006 0.8407 0.8767
1.500 0.1456 0.04434 0.03528 -0.0005 0.8386 0.8799
1.750 0.1362 0.04449 0.03546 0.0061 0.8291 0.8862
2.000 0.1704 0.04442 0.03543 0.0041 0.8259 0.8878
2.250 0.2062 0.04422 0.03527 0.0018 0.8235 0.8895
2.500 0.2167 0.04445 0.03556 0.0044 0.8153 0.8928
2.750 0.2367 0.04427 0.03542 0.0053 0.8104 0.8969
3.000 0.2589 0.04383 0.03502 0.0060 0.8074 0.9009
3.250 0.2746 0.04409 0.03535 0.0075 0.7983 0.9028
3.500 0.3087 0.04383 0.03518 0.0057 0.7938 0.9045
3.750 0.3490 0.04328 0.03472 0.0029 0.7908 0.9062
4.000 0.3578 0.04330 0.03480 0.0061 0.7792 0.9099
4.250 0.3949 0.04224 0.03382 0.0045 0.7747 0.9123
4.500 0.4017 0.04183 0.03347 0.0085 0.7614 0.9165
4.750 0.4338 0.04096 0.03269 0.0079 0.7485 0.9180
5.250 0.5001 0.03886 0.03080 0.0067 0.7260 0.9215
5.500 0.5135 0.03855 0.03057 0.0093 0.7109 0.9245
5.750 0.5151 0.03836 0.03043 0.0144 0.6957 0.9299
6.000 0.5392 0.03787 0.03006 0.0151 0.6774 0.9318
6.250 0.5647 0.03738 0.02965 0.0156 0.6544 0.9335
6.500 0.5966 0.03640 0.02870 0.0153 0.6228 0.9351
6.750 0.6672 0.03360 0.02549 0.0096 0.5324 0.9349
7.000 0.6939 0.03353 0.02465 0.0100 0.4154 0.9362
7.250 0.6965 0.03447 0.02512 0.0141 0.3403 0.9394
7.500 0.6920 0.03535 0.02570 0.0194 0.2912 0.9439
7.750 0.6988 0.03619 0.02626 0.0223 0.2437 0.9461
8.000 0.7110 0.03700 0.02684 0.0240 0.2058 0.9477
8.250 0.7244 0.03773 0.02744 0.0256 0.1779 0.9497
8.500 0.7365 0.03848 0.02808 0.0274 0.1571 0.9523
8.750 0.7458 0.03919 0.02873 0.0298 0.1418 0.9554
9.000 0.7502 0.03984 0.02936 0.0334 0.1305 0.9588
9.250 0.7660 0.04056 0.03005 0.0343 0.1189 0.9601
9.500 0.7800 0.04138 0.03082 0.0355 0.1099 0.9617
9.750 0.7958 0.04210 0.03161 0.0365 0.1019 0.9637
10.000 0.8069 0.04302 0.03247 0.0382 0.0960 0.9662
10.250 0.8187 0.04374 0.03328 0.0400 0.0905 0.9687
10.500 0.8257 0.04457 0.03413 0.0427 0.0864 0.9714
10.750 0.8410 0.04547 0.03503 0.0435 0.0827 0.9725
11.000 0.8587 0.04627 0.03594 0.0440 0.0789 0.9740
11.250 0.8747 0.04715 0.03685 0.0446 0.0756 0.9757
11.500 0.8888 0.04816 0.03781 0.0455 0.0730 0.9776
11.750 0.9050 0.04900 0.03882 0.0464 0.0703 0.9796
12.000 0.9188 0.04991 0.03982 0.0477 0.0680 0.9815
12.250 0.9327 0.05086 0.04083 0.0489 0.0661 0.9832
12.500 0.9499 0.05183 0.04181 0.0491 0.0643 0.9842
12.750 0.9688 0.05289 0.04294 0.0492 0.0625 0.9855
13.000 0.9858 0.05403 0.04430 0.0495 0.0605 0.9870
13.250 1.0008 0.05524 0.04565 0.0501 0.0587 0.9886
13.500 1.0148 0.05649 0.04700 0.0507 0.0573 0.9902
13.750 1.0276 0.05776 0.04832 0.0516 0.0561 0.9917
14.000 1.0423 0.05904 0.04960 0.0521 0.0549 0.9930
14.250 1.0507 0.06080 0.05162 0.0532 0.0537 0.9942
14.500 1.0569 0.06274 0.05384 0.0543 0.0524 0.9955
14.750 1.0624 0.06478 0.05612 0.0552 0.0512 0.9969
15.000 1.0672 0.06692 0.05844 0.0560 0.0502 0.9984
15.250 1.0711 0.06912 0.06080 0.0568 0.0493 0.9998
15.500 1.0684 0.07106 0.06286 0.0590 0.0486 1.0000
15.750 1.0657 0.07288 0.06475 0.0612 0.0480 1.0000
16.000 1.0658 0.07467 0.06655 0.0631 0.0473 1.0000
16.250 1.0463 0.07798 0.07016 0.0661 0.0468 1.0000
16.500 1.0251 0.08164 0.07411 0.0687 0.0464 1.0000
16.750 1.0026 0.08566 0.07840 0.0708 0.0460 1.0000
17.000 0.9779 0.09017 0.08316 0.0724 0.0456 1.0000
17.250 0.9503 0.09534 0.08858 0.0733 0.0454 1.0000
17.500 0.9189 0.10143 0.09491 0.0734 0.0452 1.0000
17.750 0.8809 0.10906 0.10280 0.0723 0.0452 1.0000
18.000 0.8297 0.11994 0.11395 0.0687 0.0454 1.0000
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