NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(2)-215 (naca662215-il) Reynolds number: 200,000 Max Cl/Cd: 44.82 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca662215-il-200000.txt Download as CSV file: xf-naca662215-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-215
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4837 0.10242 0.09890 -0.0634 1.0000 0.0684
-12.000 -0.4910 0.10140 0.09795 -0.0603 1.0000 0.0693
-11.750 -0.5138 0.10051 0.09715 -0.0561 0.9995 0.0699
-11.500 -0.5077 0.09508 0.09171 -0.0608 0.9963 0.0720
-11.250 -0.5250 0.08463 0.08123 -0.0713 0.9914 0.0738
-11.000 -0.5520 0.07591 0.07239 -0.0796 0.9862 0.0748
-10.750 -0.5793 0.06970 0.06596 -0.0845 0.9803 0.0762
-10.500 -0.6236 0.06704 0.06280 -0.0858 0.9707 0.0784
-10.000 -0.6145 0.05722 0.05285 -0.0875 0.9612 0.0824
-9.750 -0.5966 0.05438 0.04993 -0.0889 0.9585 0.0855
-9.500 -0.6020 0.05267 0.04800 -0.0861 0.9504 0.0891
-8.750 -0.6193 0.03793 0.03123 -0.0735 0.9318 0.0567
-8.500 -0.5915 0.03468 0.02770 -0.0737 0.9300 0.0516
-8.250 -0.5787 0.03220 0.02488 -0.0713 0.9250 0.0494
-8.000 -0.5582 0.02999 0.02228 -0.0701 0.9211 0.0481
-7.750 -0.5299 0.02823 0.02029 -0.0703 0.9187 0.0482
-7.500 -0.5005 0.02701 0.01896 -0.0710 0.9168 0.0498
-7.250 -0.4681 0.02577 0.01759 -0.0721 0.9153 0.0512
-7.000 -0.4322 0.02450 0.01619 -0.0736 0.9142 0.0523
-6.750 -0.4102 0.02383 0.01545 -0.0728 0.9106 0.0533
-6.500 -0.3866 0.02326 0.01481 -0.0722 0.9075 0.0544
-6.250 -0.3561 0.02202 0.01365 -0.0732 0.9057 0.0576
-6.000 -0.3362 0.02148 0.01313 -0.0722 0.9030 0.0604
-5.750 -0.3168 0.02098 0.01261 -0.0710 0.9006 0.0631
-5.500 -0.2975 0.02058 0.01215 -0.0697 0.8984 0.0658
-5.250 -0.3082 0.02081 0.01239 -0.0632 0.8916 0.0675
-5.000 -0.3025 0.02055 0.01216 -0.0597 0.8880 0.0720
-4.750 -0.2870 0.02030 0.01186 -0.0578 0.8857 0.0782
-4.500 -0.2721 0.01985 0.01144 -0.0559 0.8838 0.0909
-4.250 -0.2891 0.02029 0.01193 -0.0481 0.8774 0.0993
-4.000 -0.3033 0.01984 0.01195 -0.0411 0.8728 0.1780
-3.750 -0.3239 0.01811 0.01154 -0.0335 0.8694 0.4450
-3.500 -0.3162 0.01811 0.01267 -0.0283 0.8677 0.7070
-3.250 -0.3352 0.01884 0.01340 -0.0198 0.8626 0.7228
-3.000 -0.3287 0.01948 0.01398 -0.0157 0.8593 0.7457
-2.750 -0.3114 0.02037 0.01487 -0.0127 0.8570 0.7656
-2.500 -0.2911 0.02150 0.01602 -0.0097 0.8550 0.7866
-2.250 -0.2680 0.02278 0.01730 -0.0067 0.8533 0.8097
-2.000 -0.2384 0.02404 0.01854 -0.0049 0.8522 0.8257
-1.750 -0.1937 0.02542 0.01989 -0.0057 0.8516 0.8371
-1.500 -0.2304 0.02548 0.01997 0.0051 0.8446 0.8446
-1.250 -0.2187 0.02587 0.02031 0.0083 0.8413 0.8566
-1.000 -0.1824 0.02639 0.02079 0.0074 0.8396 0.8611
-0.750 -0.1486 0.02654 0.02088 0.0062 0.8377 0.8648
-0.500 -0.1157 0.02649 0.02076 0.0048 0.8361 0.8684
-0.250 -0.1370 0.02644 0.02070 0.0127 0.8290 0.8753
0.000 -0.1154 0.02649 0.02072 0.0134 0.8252 0.8781
0.250 -0.0844 0.02647 0.02066 0.0124 0.8226 0.8806
0.500 -0.0494 0.02642 0.02057 0.0107 0.8206 0.8828
0.750 -0.0086 0.02635 0.02047 0.0079 0.8192 0.8844
1.000 -0.0328 0.02628 0.02040 0.0160 0.8088 0.8904
1.250 0.0018 0.02623 0.02034 0.0144 0.8062 0.8915
1.500 0.0412 0.02618 0.02028 0.0121 0.8044 0.8925
1.750 0.0837 0.02616 0.02026 0.0092 0.8031 0.8935
2.000 0.0701 0.02625 0.02036 0.0154 0.7917 0.8985
2.250 0.1077 0.02614 0.02026 0.0134 0.7894 0.8998
2.500 0.1409 0.02607 0.02021 0.0120 0.7862 0.9015
2.750 0.1474 0.02611 0.02026 0.0149 0.7765 0.9051
3.000 0.1874 0.02589 0.02009 0.0128 0.7741 0.9063
3.250 0.2326 0.02559 0.01984 0.0099 0.7725 0.9070
3.500 0.2350 0.02576 0.02005 0.0136 0.7609 0.9110
3.750 0.2779 0.02537 0.01973 0.0111 0.7586 0.9120
4.000 0.3132 0.02506 0.01948 0.0098 0.7544 0.9138
4.250 0.3340 0.02482 0.01930 0.0108 0.7451 0.9171
4.500 0.4298 0.02205 0.01667 0.0021 0.7435 0.9133
4.750 0.5285 0.01875 0.01348 -0.0071 0.7341 0.9095
5.000 0.5907 0.01639 0.01115 -0.0109 0.7140 0.9090
5.250 0.6201 0.01546 0.01028 -0.0103 0.6946 0.9112
5.500 0.6180 0.01510 0.01000 -0.0046 0.6699 0.9171
5.750 0.6337 0.01414 0.00864 -0.0008 0.5560 0.9205
6.000 0.6149 0.01467 0.00845 0.0080 0.4409 0.9270
6.250 0.5898 0.01574 0.00893 0.0166 0.3349 0.9353
6.500 0.5679 0.01728 0.00976 0.0236 0.2047 0.9443
6.750 0.5587 0.01902 0.01078 0.0282 0.0936 0.9517
7.000 0.5696 0.01992 0.01157 0.0300 0.0756 0.9587
7.250 0.5895 0.02079 0.01248 0.0301 0.0669 0.9638
7.500 0.6071 0.02192 0.01359 0.0303 0.0614 0.9695
7.750 0.6323 0.02279 0.01452 0.0295 0.0575 0.9740
8.000 0.6595 0.02377 0.01549 0.0282 0.0531 0.9777
8.250 0.6873 0.02513 0.01677 0.0274 0.0503 0.9812
8.500 0.7212 0.02601 0.01773 0.0258 0.0486 0.9845
8.750 0.7591 0.02704 0.01881 0.0237 0.0463 0.9866
9.000 0.7969 0.02813 0.01993 0.0215 0.0440 0.9890
9.250 0.8445 0.02988 0.02165 0.0183 0.0422 0.9891
9.500 0.9073 0.03368 0.02559 0.0131 0.0413 0.9849
9.750 0.9447 0.03620 0.02838 0.0108 0.0411 0.9862
10.000 0.9745 0.03857 0.03109 0.0093 0.0408 0.9893
10.250 0.9989 0.04098 0.03385 0.0086 0.0405 0.9943
10.500 1.0323 0.04602 0.03913 0.0064 0.0415 0.9960
10.750 1.0292 0.04589 0.03920 0.0109 0.0421 1.0000
12.500 0.7735 0.07888 0.07527 0.0422 0.0854 1.0000
12.750 0.7397 0.08404 0.08055 0.0421 0.0854 1.0000
13.000 0.7053 0.08999 0.08662 0.0409 0.0854 1.0000
13.250 0.6663 0.09680 0.09354 0.0382 0.0854 1.0000
13.500 0.6241 0.10481 0.10164 0.0336 0.0855 1.0000
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Polar data table (+)
Polar graphs
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