NACA 66 (p51htip-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66 (p51htip-il) Reynolds number: 50,000 Max Cl/Cd: 22.7 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51htip-il-50000-n5.txt Download as CSV file: xf-p51htip-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3658 0.11240 0.10564 -0.0456 1.0000 0.0670
-11.500 -0.3690 0.10829 0.10156 -0.0471 1.0000 0.0650
-11.250 -0.4890 0.10755 0.10038 -0.0496 1.0000 0.0590
-11.000 -0.4817 0.10395 0.09680 -0.0493 1.0000 0.0578
-10.750 -0.4819 0.09951 0.09241 -0.0509 1.0000 0.0567
-10.500 -0.4852 0.09475 0.08770 -0.0532 1.0000 0.0556
-10.250 -0.4930 0.08941 0.08242 -0.0564 1.0000 0.0546
-10.000 -0.5068 0.08437 0.07744 -0.0590 1.0000 0.0537
-9.750 -0.5262 0.08031 0.07343 -0.0598 1.0000 0.0528
-9.500 -0.5521 0.07754 0.07070 -0.0579 1.0000 0.0520
-9.250 -0.5832 0.07589 0.06910 -0.0535 1.0000 0.0515
-9.000 -0.6147 0.07461 0.06785 -0.0479 1.0000 0.0511
-8.750 -0.6411 0.07270 0.06589 -0.0432 1.0000 0.0506
-8.500 -0.6652 0.07042 0.06350 -0.0386 1.0000 0.0499
-8.250 -0.6848 0.06788 0.06078 -0.0343 1.0000 0.0494
-8.000 -0.6999 0.06517 0.05783 -0.0302 1.0000 0.0490
-7.750 -0.6989 0.06173 0.05408 -0.0290 0.9963 0.0491
-7.500 -0.6900 0.05856 0.05063 -0.0287 0.9917 0.0502
-7.250 -0.6801 0.05546 0.04719 -0.0282 0.9872 0.0512
-7.000 -0.6689 0.05238 0.04371 -0.0274 0.9835 0.0522
-6.750 -0.6577 0.04945 0.04036 -0.0261 0.9796 0.0526
-6.500 -0.6420 0.04652 0.03695 -0.0251 0.9760 0.0528
-6.250 -0.6218 0.04378 0.03372 -0.0247 0.9730 0.0532
-6.000 -0.6037 0.04159 0.03110 -0.0235 0.9696 0.0546
-5.500 -0.5595 0.03795 0.02642 -0.0218 0.9640 0.0590
-5.250 -0.5323 0.03599 0.02423 -0.0219 0.9621 0.0604
-5.000 -0.5029 0.03439 0.02251 -0.0223 0.9605 0.0627
-4.750 -0.4756 0.03330 0.02129 -0.0223 0.9584 0.0673
-4.500 -0.4489 0.03241 0.02011 -0.0218 0.9560 0.0717
-4.250 -0.4219 0.03138 0.01906 -0.0215 0.9539 0.0753
-4.000 -0.3985 0.03062 0.01819 -0.0209 0.9516 0.0810
-3.750 -0.3762 0.02991 0.01738 -0.0202 0.9492 0.0894
-3.500 -0.3529 0.02923 0.01656 -0.0198 0.9468 0.0996
-3.000 -0.3224 0.02726 0.01512 -0.0166 0.9407 0.1699
-2.750 -0.3255 0.02538 0.01628 -0.0085 0.9385 0.7291
-2.500 -0.1456 0.02987 0.01998 -0.0260 0.9493 0.9463
-2.250 -0.1035 0.02976 0.01955 -0.0298 0.9477 0.9551
-2.000 -0.0648 0.02969 0.01923 -0.0331 0.9461 0.9627
-1.750 -0.0347 0.02961 0.01897 -0.0347 0.9434 0.9707
-1.500 -0.0015 0.02951 0.01869 -0.0370 0.9406 0.9771
-1.250 0.0303 0.02949 0.01853 -0.0391 0.9379 0.9836
-1.000 0.0658 0.02945 0.01837 -0.0419 0.9354 0.9888
-0.750 0.1010 0.02951 0.01832 -0.0446 0.9331 0.9940
-0.500 0.1340 0.02954 0.01828 -0.0469 0.9304 0.9991
-0.250 0.1467 0.02966 0.01836 -0.0453 0.9255 1.0000
0.000 0.1649 0.02981 0.01848 -0.0446 0.9211 1.0000
0.250 0.1892 0.03002 0.01866 -0.0451 0.9176 1.0000
0.500 0.1942 0.03018 0.01881 -0.0419 0.9115 1.0000
0.750 0.2120 0.03039 0.01902 -0.0411 0.9066 1.0000
1.000 0.2369 0.03065 0.01929 -0.0415 0.9028 1.0000
1.250 0.2394 0.03083 0.01949 -0.0378 0.8955 1.0000
1.500 0.2604 0.03109 0.01978 -0.0375 0.8905 1.0000
1.750 0.2715 0.03133 0.02006 -0.0354 0.8841 1.0000
2.000 0.2866 0.03158 0.02036 -0.0339 0.8776 1.0000
2.250 0.3078 0.03187 0.02073 -0.0334 0.8720 1.0000
2.500 0.3152 0.03210 0.02102 -0.0306 0.8637 1.0000
2.750 0.3427 0.03243 0.02145 -0.0312 0.8583 1.0000
3.000 0.3461 0.03264 0.02173 -0.0275 0.8486 1.0000
3.250 0.3665 0.03294 0.02216 -0.0267 0.8413 1.0000
3.500 0.3814 0.03319 0.02251 -0.0250 0.8322 1.0000
3.750 0.3940 0.03345 0.02288 -0.0228 0.8225 1.0000
4.000 0.4247 0.03372 0.02333 -0.0235 0.8149 1.0000
4.250 0.4349 0.03394 0.02367 -0.0208 0.8031 1.0000
4.500 0.4518 0.03415 0.02407 -0.0192 0.7918 1.0000
4.750 0.4772 0.03429 0.02443 -0.0187 0.7809 1.0000
5.000 0.5127 0.03424 0.02469 -0.0196 0.7702 1.0000
5.250 0.5597 0.03240 0.02327 -0.0196 0.7401 1.0000
5.500 0.5764 0.02853 0.01952 -0.0117 0.6643 1.0000
5.750 0.5654 0.02830 0.01931 -0.0049 0.6089 1.0000
6.000 0.6043 0.02662 0.01518 0.0005 0.1976 1.0000
6.500 0.6040 0.02982 0.01745 0.0076 0.1043 1.0000
6.750 0.6138 0.03108 0.01860 0.0098 0.0905 1.0000
7.000 0.6273 0.03224 0.01982 0.0117 0.0833 1.0000
7.250 0.6442 0.03341 0.02100 0.0132 0.0765 1.0000
7.500 0.6683 0.03450 0.02223 0.0139 0.0697 1.0000
7.750 0.7096 0.03576 0.02360 0.0128 0.0642 1.0000
8.000 0.7760 0.03800 0.02607 0.0081 0.0590 1.0000
8.500 0.8444 0.04237 0.03096 0.0062 0.0527 1.0000
8.750 0.8716 0.04509 0.03391 0.0060 0.0514 1.0000
9.000 0.8940 0.04834 0.03736 0.0062 0.0503 1.0000
9.250 0.9036 0.05080 0.04031 0.0085 0.0494 1.0000
9.500 0.9087 0.05339 0.04337 0.0110 0.0484 1.0000
9.750 0.9102 0.05616 0.04660 0.0137 0.0474 1.0000
10.000 0.9083 0.05908 0.04988 0.0165 0.0467 1.0000
10.250 0.9034 0.06208 0.05320 0.0193 0.0466 1.0000
10.500 0.8935 0.06506 0.05646 0.0223 0.0466 1.0000
10.750 0.8810 0.06819 0.05982 0.0250 0.0466 1.0000
11.000 0.8662 0.07159 0.06344 0.0271 0.0468 1.0000
11.250 0.8493 0.07529 0.06734 0.0286 0.0469 1.0000
11.500 0.8307 0.07936 0.07160 0.0292 0.0472 1.0000
11.750 0.8093 0.08408 0.07647 0.0289 0.0474 1.0000
12.000 0.7883 0.08933 0.08184 0.0276 0.0477 1.0000
12.250 0.7688 0.09509 0.08769 0.0252 0.0482 1.0000
12.500 0.7502 0.10160 0.09424 0.0219 0.0486 1.0000
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Polar data table (+)
Polar graphs
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