NACA 66(2)-415 (naca662415-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(2)-415 (naca662415-il) Reynolds number: 500,000 Max Cl/Cd: 93.96 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca662415-il-500000.txt Download as CSV file: xf-naca662415-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(2)-415
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3235 0.08437 0.08188 -0.1054 0.9575 0.0301
-11.750 -0.3357 0.07236 0.06983 -0.1173 0.9487 0.0308
-11.500 -0.3687 0.06192 0.05919 -0.1264 0.9353 0.0308
-11.250 -0.3954 0.05674 0.05381 -0.1280 0.9227 0.0306
-9.500 -0.5355 0.03235 0.02731 -0.1003 0.8668 0.0266
-9.250 -0.5285 0.02960 0.02426 -0.0980 0.8631 0.0262
-9.000 -0.5177 0.02731 0.02167 -0.0959 0.8594 0.0263
-8.750 -0.5021 0.02569 0.01979 -0.0944 0.8559 0.0267
-8.500 -0.4846 0.02492 0.01876 -0.0929 0.8528 0.0273
-8.250 -0.4658 0.02364 0.01721 -0.0918 0.8501 0.0277
-8.000 -0.4405 0.02117 0.01455 -0.0920 0.8478 0.0281
-7.750 -0.4147 0.01979 0.01313 -0.0921 0.8452 0.0287
-7.500 -0.3898 0.01894 0.01224 -0.0920 0.8426 0.0293
-7.250 -0.3651 0.01829 0.01156 -0.0918 0.8401 0.0302
-7.000 -0.3402 0.01773 0.01094 -0.0916 0.8378 0.0314
-6.750 -0.3144 0.01706 0.01019 -0.0915 0.8358 0.0322
-6.500 -0.2889 0.01649 0.00954 -0.0913 0.8339 0.0329
-6.250 -0.2643 0.01605 0.00905 -0.0910 0.8318 0.0335
-6.000 -0.2419 0.01515 0.00814 -0.0904 0.8296 0.0344
-5.750 -0.2218 0.01448 0.00749 -0.0894 0.8272 0.0358
-5.500 -0.2000 0.01410 0.00711 -0.0887 0.8249 0.0372
-5.250 -0.1780 0.01373 0.00672 -0.0879 0.8229 0.0387
-5.000 -0.1554 0.01339 0.00634 -0.0872 0.8209 0.0401
-4.750 -0.1320 0.01311 0.00601 -0.0867 0.8191 0.0411
-4.500 -0.1117 0.01264 0.00550 -0.0857 0.8171 0.0433
-4.250 -0.0897 0.01235 0.00523 -0.0849 0.8152 0.0463
-4.000 -0.0662 0.01215 0.00503 -0.0844 0.8132 0.0493
-3.750 -0.0430 0.01189 0.00477 -0.0838 0.8112 0.0536
-3.500 -0.0189 0.01167 0.00457 -0.0834 0.8094 0.0617
-3.250 -0.0042 0.01067 0.00421 -0.0819 0.8074 0.2135
-3.000 0.0014 0.00877 0.00367 -0.0793 0.8053 0.5556
-2.750 0.0248 0.00861 0.00391 -0.0784 0.8039 0.6867
-2.500 0.0530 0.00876 0.00404 -0.0785 0.8027 0.7111
-2.250 0.0810 0.00901 0.00426 -0.0785 0.8013 0.7321
-2.000 0.1067 0.00929 0.00460 -0.0779 0.7996 0.7495
-1.750 0.1329 0.00959 0.00494 -0.0774 0.7979 0.7620
-1.500 0.1587 0.00989 0.00529 -0.0767 0.7963 0.7718
-1.250 0.1861 0.01007 0.00544 -0.0767 0.7948 0.7790
-1.000 0.2124 0.01026 0.00567 -0.0762 0.7933 0.7847
-0.750 0.2393 0.01047 0.00589 -0.0760 0.7919 0.7905
-0.500 0.2679 0.01053 0.00591 -0.0764 0.7904 0.7946
-0.250 0.2968 0.01054 0.00590 -0.0769 0.7891 0.7972
0.000 0.3251 0.01056 0.00592 -0.0772 0.7880 0.7989
0.250 0.3543 0.01060 0.00595 -0.0777 0.7866 0.8004
0.500 0.3815 0.01064 0.00600 -0.0778 0.7845 0.8017
0.750 0.4077 0.01066 0.00604 -0.0778 0.7818 0.8032
1.000 0.4351 0.01066 0.00606 -0.0780 0.7791 0.8048
1.250 0.4637 0.01063 0.00603 -0.0784 0.7766 0.8066
1.500 0.4931 0.01058 0.00598 -0.0790 0.7745 0.8082
1.750 0.5234 0.01055 0.00594 -0.0798 0.7727 0.8097
2.000 0.5544 0.01056 0.00593 -0.0807 0.7708 0.8111
2.250 0.5803 0.01057 0.00598 -0.0807 0.7673 0.8127
2.500 0.6072 0.01039 0.00585 -0.0805 0.7620 0.8140
2.750 0.6393 0.01010 0.00553 -0.0812 0.7566 0.8153
3.000 0.6647 0.00995 0.00542 -0.0807 0.7493 0.8169
3.250 0.6943 0.00970 0.00517 -0.0810 0.7422 0.8184
3.500 0.7204 0.00958 0.00509 -0.0807 0.7350 0.8200
3.750 0.7488 0.00934 0.00483 -0.0807 0.7252 0.8217
4.000 0.7720 0.00915 0.00467 -0.0797 0.7117 0.8237
4.250 0.7955 0.00900 0.00452 -0.0788 0.6952 0.8258
4.500 0.8188 0.00895 0.00447 -0.0780 0.6785 0.8279
4.750 0.8381 0.00892 0.00444 -0.0763 0.6496 0.8298
5.000 0.8418 0.00924 0.00444 -0.0714 0.5692 0.8322
5.250 0.8284 0.01010 0.00487 -0.0634 0.4880 0.8358
5.500 0.8129 0.01106 0.00548 -0.0554 0.4141 0.8402
5.750 0.8017 0.01227 0.00627 -0.0488 0.3337 0.8444
6.000 0.7915 0.01356 0.00716 -0.0428 0.2476 0.8480
6.250 0.7820 0.01509 0.00817 -0.0372 0.1474 0.8519
6.500 0.7783 0.01657 0.00919 -0.0329 0.0649 0.8560
6.750 0.7914 0.01732 0.00984 -0.0310 0.0487 0.8595
7.000 0.8052 0.01797 0.01049 -0.0292 0.0428 0.8626
7.250 0.8214 0.01850 0.01107 -0.0277 0.0397 0.8659
7.500 0.8357 0.01916 0.01176 -0.0261 0.0371 0.8697
7.750 0.8486 0.01998 0.01261 -0.0243 0.0346 0.8739
8.000 0.8640 0.02060 0.01330 -0.0229 0.0332 0.8779
8.250 0.8777 0.02128 0.01404 -0.0212 0.0318 0.8822
8.500 0.8906 0.02209 0.01488 -0.0195 0.0302 0.8871
8.750 0.8967 0.02341 0.01624 -0.0171 0.0286 0.8922
9.000 0.9126 0.02396 0.01688 -0.0158 0.0277 0.8969
9.250 0.9270 0.02471 0.01769 -0.0144 0.0266 0.9025
9.500 0.9406 0.02554 0.01859 -0.0129 0.0258 0.9082
9.750 0.9532 0.02636 0.01946 -0.0112 0.0250 0.9146
10.000 0.9660 0.02731 0.02043 -0.0098 0.0241 0.9216
10.250 0.9782 0.02869 0.02184 -0.0080 0.0231 0.9280
10.500 0.9939 0.02939 0.02264 -0.0068 0.0228 0.9370
10.750 1.0102 0.03015 0.02351 -0.0055 0.0224 0.9484
11.000 1.0306 0.03097 0.02444 -0.0053 0.0217 0.9639
11.250 1.0550 0.03192 0.02547 -0.0060 0.0211 1.0000
11.500 1.0757 0.03294 0.02653 -0.0060 0.0205 1.0000
11.750 1.0937 0.03397 0.02761 -0.0058 0.0198 1.0000
12.000 1.1151 0.03513 0.02881 -0.0058 0.0195 1.0000
12.250 1.1412 0.03651 0.03020 -0.0062 0.0190 1.0000
12.500 1.1762 0.03888 0.03272 -0.0074 0.0186 1.0000
12.750 1.1848 0.04038 0.03441 -0.0061 0.0184 1.0000
13.000 1.1972 0.04232 0.03653 -0.0052 0.0183 1.0000
13.250 1.2042 0.04439 0.03882 -0.0039 0.0181 1.0000
13.500 1.2093 0.04679 0.04143 -0.0026 0.0179 1.0000
13.750 1.2110 0.04950 0.04437 -0.0011 0.0179 1.0000
14.000 1.2082 0.05258 0.04769 0.0005 0.0178 1.0000
14.250 1.2009 0.05576 0.05111 0.0022 0.0177 1.0000
14.500 1.1918 0.05912 0.05468 0.0037 0.0176 1.0000
14.750 1.1766 0.06319 0.05901 0.0051 0.0175 1.0000
15.000 1.1610 0.06756 0.06360 0.0059 0.0175 1.0000
15.250 1.1424 0.07232 0.06859 0.0063 0.0174 1.0000
15.500 1.1207 0.07790 0.07440 0.0061 0.0175 1.0000
15.750 1.0974 0.08403 0.08073 0.0051 0.0176 1.0000
16.000 1.0764 0.09029 0.08716 0.0033 0.0179 1.0000
16.250 1.0514 0.09762 0.09469 0.0004 0.0179 1.0000
16.500 1.0261 0.10574 0.10297 -0.0035 0.0181 1.0000
16.750 1.0017 0.11443 0.11179 -0.0082 0.0183 1.0000
17.000 0.9928 0.12093 0.11842 -0.0117 0.0192 1.0000
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