NACA 66-018 (naca66-018-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66-018 (naca66-018-il) Reynolds number: 50,000 Max Cl/Cd: 15.27 at α=11° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66-018-il-50000-n5.txt Download as CSV file: xf-naca66-018-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-018
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
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6053 0.11247 0.10475 -0.0635 1.0000 0.0550
-15.000 -0.6270 0.10475 0.09696 -0.0676 1.0000 0.0547
-14.750 -0.6517 0.09758 0.08969 -0.0711 1.0000 0.0544
-14.500 -0.6772 0.09125 0.08321 -0.0736 1.0000 0.0541
-14.250 -0.7021 0.08572 0.07751 -0.0751 1.0000 0.0539
-14.000 -0.7252 0.08089 0.07251 -0.0756 1.0000 0.0538
-13.750 -0.7457 0.07670 0.06812 -0.0754 1.0000 0.0537
-13.500 -0.7629 0.07314 0.06435 -0.0745 1.0000 0.0536
-13.250 -0.7802 0.06993 0.06093 -0.0728 1.0000 0.0537
-13.000 -0.7964 0.06730 0.05808 -0.0703 1.0000 0.0539
-12.750 -0.8151 0.06528 0.05587 -0.0666 1.0000 0.0541
-12.500 -0.8339 0.06381 0.05423 -0.0622 1.0000 0.0542
-12.250 -0.8541 0.06252 0.05275 -0.0572 1.0000 0.0545
-12.000 -0.8724 0.06128 0.05129 -0.0521 1.0000 0.0549
-11.750 -0.8846 0.05993 0.04976 -0.0477 1.0000 0.0553
-11.500 -0.8637 0.05776 0.04755 -0.0484 0.9964 0.0570
-11.250 -0.8428 0.05565 0.04524 -0.0490 0.9920 0.0587
-11.000 -0.8168 0.05355 0.04284 -0.0498 0.9882 0.0607
-10.750 -0.7800 0.05159 0.04052 -0.0514 0.9856 0.0629
-10.500 -0.7380 0.05018 0.03903 -0.0535 0.9836 0.0665
-10.250 -0.6991 0.04923 0.03796 -0.0549 0.9810 0.0707
-10.000 -0.6538 0.04867 0.03724 -0.0563 0.9788 0.0756
-9.750 -0.6243 0.04786 0.03643 -0.0570 0.9759 0.0817
-9.500 -0.5974 0.04697 0.03544 -0.0575 0.9731 0.0884
-9.250 -0.5775 0.04593 0.03438 -0.0575 0.9700 0.0963
-9.000 -0.5646 0.04480 0.03330 -0.0567 0.9661 0.1057
-8.750 -0.5523 0.04349 0.03208 -0.0560 0.9628 0.1198
-8.500 -0.5427 0.04189 0.03073 -0.0553 0.9599 0.1461
-8.250 -0.5435 0.04026 0.02953 -0.0530 0.9556 0.1914
-8.000 -0.5496 0.03853 0.02846 -0.0499 0.9511 0.2744
-7.750 -0.5261 0.03906 0.03017 -0.0474 0.9487 0.4381
-7.500 -0.4785 0.04223 0.03346 -0.0463 0.9470 0.5322
-7.250 -0.4620 0.04446 0.03558 -0.0424 0.9430 0.5811
-7.000 -0.4515 0.04620 0.03717 -0.0383 0.9390 0.6163
-6.750 -0.4232 0.04784 0.03856 -0.0370 0.9365 0.6390
-6.500 -0.3992 0.04839 0.03888 -0.0364 0.9343 0.6549
-6.250 -0.3749 0.04874 0.03901 -0.0362 0.9324 0.6696
-6.000 -0.3748 0.04907 0.03922 -0.0318 0.9280 0.6835
-5.750 -0.3602 0.04935 0.03934 -0.0300 0.9246 0.6965
-5.500 -0.3250 0.04971 0.03950 -0.0311 0.9226 0.7052
-5.250 -0.3074 0.04975 0.03938 -0.0302 0.9202 0.7174
-5.000 -0.2832 0.04982 0.03927 -0.0303 0.9184 0.7280
-4.750 -0.2638 0.04997 0.03930 -0.0292 0.9162 0.7365
-4.500 -0.2724 0.05010 0.03937 -0.0237 0.9124 0.7487
-4.000 -0.2368 0.05012 0.03915 -0.0216 0.9071 0.7660
-3.500 -0.1987 0.05001 0.03882 -0.0204 0.9031 0.7825
-3.250 -0.1624 0.04991 0.03860 -0.0226 0.9020 0.7871
-3.000 -0.1654 0.05001 0.03867 -0.0179 0.8983 0.7955
-2.750 -0.1584 0.04997 0.03857 -0.0151 0.8950 0.8026
-2.500 -0.1377 0.04993 0.03846 -0.0148 0.8928 0.8083
-2.250 -0.1398 0.04990 0.03838 -0.0106 0.8896 0.8172
-2.000 -0.1057 0.04977 0.03818 -0.0127 0.8877 0.8209
-1.750 -0.0777 0.04970 0.03805 -0.0137 0.8858 0.8259
-1.500 -0.0984 0.04978 0.03812 -0.0060 0.8810 0.8345
-1.250 -0.0738 0.04971 0.03801 -0.0064 0.8779 0.8381
-1.000 -0.0538 0.04967 0.03795 -0.0061 0.8748 0.8425
-0.750 -0.0403 0.04965 0.03790 -0.0046 0.8717 0.8479
-0.500 -0.0249 0.04962 0.03784 -0.0034 0.8688 0.8527
-0.250 -0.0100 0.04962 0.03785 -0.0021 0.8649 0.8562
0.000 0.0001 0.04962 0.03785 0.0000 0.8603 0.8602
0.250 0.0110 0.04962 0.03785 0.0020 0.8562 0.8647
0.500 0.0216 0.04962 0.03783 0.0040 0.8524 0.8691
0.750 0.0411 0.04965 0.03789 0.0044 0.8481 0.8717
1.000 0.0534 0.04966 0.03794 0.0061 0.8424 0.8749
1.250 0.0731 0.04970 0.03801 0.0065 0.8379 0.8780
1.500 0.0975 0.04977 0.03810 0.0062 0.8342 0.8810
1.750 0.0764 0.04969 0.03804 0.0140 0.8259 0.8860
2.000 0.1041 0.04975 0.03816 0.0130 0.8207 0.8878
2.250 0.1379 0.04987 0.03836 0.0109 0.8170 0.8897
2.500 0.1376 0.04992 0.03845 0.0148 0.8084 0.8928
2.750 0.1576 0.04996 0.03856 0.0153 0.8025 0.8950
3.000 0.1693 0.05001 0.03867 0.0172 0.7960 0.8981
3.250 0.1628 0.04990 0.03860 0.0225 0.7872 0.9021
3.500 0.1964 0.04998 0.03879 0.0208 0.7822 0.9033
4.000 0.2350 0.05009 0.03911 0.0219 0.7658 0.9072
4.500 0.2713 0.05009 0.03936 0.0238 0.7485 0.9124
4.750 0.2648 0.04997 0.03930 0.0290 0.7365 0.9161
5.000 0.2875 0.04975 0.03921 0.0297 0.7291 0.9184
5.250 0.3058 0.04973 0.03935 0.0305 0.7173 0.9203
5.500 0.3245 0.04968 0.03947 0.0312 0.7053 0.9227
5.750 0.3658 0.04924 0.03925 0.0292 0.6976 0.9244
6.000 0.3739 0.04906 0.03922 0.0320 0.6834 0.9281
6.250 0.3743 0.04872 0.03899 0.0363 0.6695 0.9326
6.500 0.3990 0.04837 0.03887 0.0365 0.6549 0.9345
6.750 0.4232 0.04781 0.03854 0.0370 0.6389 0.9367
7.000 0.4531 0.04609 0.03707 0.0382 0.6163 0.9390
7.250 0.4623 0.04441 0.03553 0.0424 0.5811 0.9431
7.500 0.4788 0.04221 0.03344 0.0463 0.5326 0.9471
7.750 0.5265 0.03900 0.03011 0.0474 0.4376 0.9488
8.000 0.5495 0.03851 0.02843 0.0499 0.2729 0.9512
8.250 0.5440 0.04023 0.02949 0.0530 0.1919 0.9557
8.500 0.5430 0.04189 0.03071 0.0553 0.1454 0.9600
8.750 0.5529 0.04347 0.03206 0.0559 0.1195 0.9629
9.000 0.5652 0.04478 0.03327 0.0566 0.1053 0.9663
9.250 0.5781 0.04591 0.03435 0.0574 0.0961 0.9702
9.500 0.5983 0.04694 0.03542 0.0574 0.0882 0.9732
9.750 0.6251 0.04783 0.03640 0.0569 0.0815 0.9760
10.000 0.6550 0.04864 0.03720 0.0562 0.0754 0.9789
10.250 0.6994 0.04920 0.03792 0.0548 0.0707 0.9811
10.500 0.7380 0.05017 0.03902 0.0534 0.0662 0.9838
10.750 0.7810 0.05158 0.04050 0.0512 0.0628 0.9857
11.000 0.8177 0.05354 0.04283 0.0497 0.0606 0.9884
11.250 0.8444 0.05568 0.04529 0.0488 0.0590 0.9921
11.500 0.8649 0.05787 0.04770 0.0482 0.0572 0.9965
11.750 0.8791 0.05986 0.04979 0.0485 0.0556 1.0000
12.000 0.8772 0.06130 0.05126 0.0516 0.0549 1.0000
12.250 0.8557 0.06250 0.05270 0.0570 0.0544 1.0000
12.500 0.8364 0.06378 0.05417 0.0620 0.0542 1.0000
12.750 0.8183 0.06522 0.05577 0.0664 0.0541 1.0000
13.000 0.7994 0.06720 0.05794 0.0701 0.0538 1.0000
13.250 0.7826 0.06982 0.06079 0.0726 0.0537 1.0000
13.500 0.7658 0.07300 0.06419 0.0743 0.0536 1.0000
13.750 0.7464 0.07674 0.06815 0.0752 0.0535 1.0000
14.000 0.7269 0.08086 0.07245 0.0755 0.0536 1.0000
14.250 0.7054 0.08554 0.07731 0.0750 0.0538 1.0000
14.500 0.6803 0.09106 0.08301 0.0735 0.0539 1.0000
14.750 0.6549 0.09736 0.08945 0.0711 0.0542 1.0000
15.000 0.6290 0.10466 0.09686 0.0675 0.0545 1.0000
15.250 0.6090 0.11208 0.10435 0.0636 0.0549 1.0000
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