NACA 642-015 AIRFOIL (n64015-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 642-015 AIRFOIL (n64015-il) Reynolds number: 100,000 Max Cl/Cd: 35.12 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64015-il-100000-n5.txt Download as CSV file: xf-n64015-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 642-015 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.7981 0.10914 0.10360 -0.0125 1.0000 0.0334
-14.750 -0.8282 0.09904 0.09334 -0.0190 1.0000 0.0332
-14.500 -0.8565 0.09053 0.08465 -0.0242 1.0000 0.0331
-14.250 -0.8809 0.08351 0.07744 -0.0280 1.0000 0.0329
-14.000 -0.9043 0.07722 0.07092 -0.0310 1.0000 0.0329
-13.750 -0.9233 0.07191 0.06538 -0.0330 1.0000 0.0329
-13.500 -0.9404 0.06715 0.06036 -0.0343 1.0000 0.0330
-13.250 -0.9554 0.06285 0.05578 -0.0350 1.0000 0.0331
-13.000 -0.9660 0.05914 0.05181 -0.0351 1.0000 0.0332
-12.750 -0.9758 0.05568 0.04803 -0.0348 1.0000 0.0334
-12.500 -0.9755 0.05277 0.04494 -0.0344 1.0000 0.0338
-12.250 -0.9700 0.05030 0.04233 -0.0339 1.0000 0.0342
-12.000 -0.9634 0.04812 0.04003 -0.0333 1.0000 0.0347
-11.750 -0.9564 0.04624 0.03806 -0.0327 1.0000 0.0356
-11.500 -0.9480 0.04433 0.03600 -0.0319 1.0000 0.0365
-11.250 -0.9382 0.04250 0.03399 -0.0311 1.0000 0.0377
-11.000 -0.9249 0.04063 0.03191 -0.0303 1.0000 0.0388
-10.750 -0.9083 0.03884 0.02986 -0.0297 1.0000 0.0399
-10.500 -0.8877 0.03717 0.02804 -0.0292 1.0000 0.0409
-10.250 -0.8673 0.03568 0.02659 -0.0289 1.0000 0.0422
-10.000 -0.8498 0.03441 0.02531 -0.0284 1.0000 0.0438
-9.750 -0.8322 0.03321 0.02403 -0.0277 1.0000 0.0459
-9.500 -0.8133 0.03207 0.02276 -0.0270 1.0000 0.0480
-9.250 -0.7961 0.03083 0.02153 -0.0263 1.0000 0.0502
-9.000 -0.7812 0.02970 0.02044 -0.0253 1.0000 0.0522
-8.750 -0.7667 0.02867 0.01939 -0.0243 1.0000 0.0551
-8.500 -0.7520 0.02773 0.01837 -0.0231 1.0000 0.0585
-8.250 -0.7426 0.02664 0.01736 -0.0215 1.0000 0.0615
-8.000 -0.7328 0.02577 0.01649 -0.0197 1.0000 0.0651
-7.750 -0.7236 0.02500 0.01570 -0.0176 1.0000 0.0696
-7.500 -0.7147 0.02412 0.01490 -0.0158 0.9913 0.0751
-7.250 -0.6873 0.02303 0.01381 -0.0174 0.9694 0.0859
-7.000 -0.6611 0.02194 0.01278 -0.0187 0.9529 0.1040
-6.750 -0.6397 0.02081 0.01182 -0.0190 0.9373 0.1361
-6.500 -0.6248 0.01959 0.01090 -0.0181 0.9216 0.1915
-6.250 -0.6159 0.01827 0.01006 -0.0162 0.9064 0.2775
-6.000 -0.6072 0.01729 0.00976 -0.0135 0.8928 0.3879
-5.750 -0.5885 0.01712 0.00978 -0.0117 0.8817 0.4655
-5.500 -0.5674 0.01712 0.00974 -0.0102 0.8713 0.5052
-5.250 -0.5454 0.01722 0.00980 -0.0089 0.8609 0.5355
-5.000 -0.5227 0.01735 0.00982 -0.0075 0.8522 0.5601
-4.750 -0.4986 0.01756 0.00999 -0.0063 0.8425 0.5797
-4.500 -0.4741 0.01782 0.01018 -0.0051 0.8343 0.5978
-4.250 -0.4493 0.01807 0.01038 -0.0040 0.8255 0.6138
-4.000 -0.4246 0.01815 0.01036 -0.0030 0.8178 0.6261
-3.750 -0.3983 0.01818 0.01029 -0.0025 0.8095 0.6341
-3.500 -0.3732 0.01801 0.00998 -0.0021 0.8026 0.6409
-3.250 -0.3462 0.01797 0.00988 -0.0019 0.7944 0.6456
-3.000 -0.3205 0.01784 0.00960 -0.0014 0.7882 0.6517
-2.750 -0.2946 0.01772 0.00940 -0.0013 0.7799 0.6577
-2.500 -0.2677 0.01767 0.00929 -0.0009 0.7734 0.6624
-2.250 -0.2415 0.01757 0.00910 -0.0008 0.7665 0.6682
-2.000 -0.2153 0.01744 0.00888 -0.0007 0.7598 0.6735
-1.750 -0.1881 0.01738 0.00877 -0.0004 0.7548 0.6774
-1.500 -0.1613 0.01733 0.00869 -0.0004 0.7473 0.6825
-1.250 -0.1352 0.01720 0.00846 -0.0004 0.7413 0.6887
-1.000 -0.1078 0.01717 0.00842 -0.0002 0.7357 0.6923
-0.750 -0.0808 0.01715 0.00840 -0.0002 0.7290 0.6969
-0.500 -0.0541 0.01708 0.00827 -0.0001 0.7240 0.7029
-0.250 -0.0270 0.01708 0.00826 -0.0001 0.7189 0.7079
0.000 0.0000 0.01712 0.00833 0.0000 0.7128 0.7128
0.250 0.0269 0.01708 0.00826 0.0001 0.7079 0.7190
0.500 0.0540 0.01708 0.00827 0.0001 0.7029 0.7240
0.750 0.0808 0.01715 0.00840 0.0002 0.6969 0.7290
1.000 0.1078 0.01717 0.00842 0.0002 0.6923 0.7357
1.250 0.1351 0.01720 0.00846 0.0004 0.6887 0.7413
1.500 0.1613 0.01733 0.00869 0.0004 0.6825 0.7473
1.750 0.1881 0.01738 0.00877 0.0004 0.6774 0.7548
2.000 0.2152 0.01744 0.00888 0.0007 0.6735 0.7598
2.250 0.2415 0.01757 0.00910 0.0008 0.6682 0.7665
2.500 0.2677 0.01767 0.00929 0.0009 0.6624 0.7734
2.750 0.2946 0.01772 0.00940 0.0013 0.6577 0.7799
3.000 0.3205 0.01784 0.00960 0.0014 0.6517 0.7882
3.250 0.3461 0.01797 0.00988 0.0019 0.6456 0.7944
3.500 0.3732 0.01801 0.00998 0.0021 0.6410 0.8026
3.750 0.3983 0.01818 0.01029 0.0025 0.6342 0.8095
4.000 0.4246 0.01815 0.01036 0.0030 0.6261 0.8178
4.250 0.4493 0.01807 0.01038 0.0039 0.6138 0.8255
4.500 0.4742 0.01782 0.01018 0.0051 0.5979 0.8343
4.750 0.4986 0.01756 0.00999 0.0063 0.5797 0.8425
5.000 0.5228 0.01734 0.00982 0.0075 0.5601 0.8522
5.250 0.5454 0.01722 0.00980 0.0088 0.5356 0.8609
5.500 0.5674 0.01712 0.00974 0.0102 0.5052 0.8713
5.750 0.5885 0.01712 0.00977 0.0117 0.4654 0.8818
6.000 0.6073 0.01729 0.00976 0.0134 0.3885 0.8928
6.250 0.6160 0.01826 0.01005 0.0161 0.2778 0.9064
6.500 0.6250 0.01959 0.01090 0.0181 0.1914 0.9216
6.750 0.6399 0.02081 0.01182 0.0189 0.1361 0.9373
7.000 0.6614 0.02194 0.01278 0.0186 0.1039 0.9529
7.250 0.6875 0.02303 0.01381 0.0174 0.0859 0.9694
7.500 0.7150 0.02412 0.01490 0.0158 0.0751 0.9916
7.750 0.7238 0.02500 0.01570 0.0176 0.0695 1.0000
8.000 0.7333 0.02577 0.01649 0.0196 0.0649 1.0000
8.250 0.7431 0.02664 0.01736 0.0214 0.0614 1.0000
8.500 0.7524 0.02775 0.01837 0.0231 0.0583 1.0000
8.750 0.7673 0.02867 0.01939 0.0242 0.0550 1.0000
9.000 0.7819 0.02970 0.02044 0.0252 0.0522 1.0000
9.250 0.7967 0.03085 0.02155 0.0262 0.0500 1.0000
9.500 0.8143 0.03208 0.02277 0.0269 0.0481 1.0000
9.750 0.8330 0.03323 0.02404 0.0276 0.0458 1.0000
10.000 0.8507 0.03443 0.02532 0.0282 0.0437 1.0000
10.250 0.8679 0.03569 0.02659 0.0288 0.0421 1.0000
10.500 0.8886 0.03718 0.02805 0.0291 0.0409 1.0000
10.750 0.9094 0.03887 0.02989 0.0295 0.0399 1.0000
11.000 0.9258 0.04066 0.03194 0.0302 0.0388 1.0000
11.250 0.9387 0.04250 0.03399 0.0309 0.0375 1.0000
11.500 0.9492 0.04438 0.03605 0.0317 0.0365 1.0000
11.750 0.9574 0.04625 0.03806 0.0325 0.0355 1.0000
12.000 0.9647 0.04825 0.04019 0.0332 0.0349 1.0000
12.250 0.9712 0.05033 0.04237 0.0337 0.0342 1.0000
12.500 0.9764 0.05281 0.04499 0.0342 0.0338 1.0000
12.750 0.9767 0.05575 0.04811 0.0346 0.0334 1.0000
13.000 0.9679 0.05914 0.05180 0.0349 0.0332 1.0000
13.250 0.9561 0.06296 0.05590 0.0348 0.0331 1.0000
13.500 0.9423 0.06715 0.06036 0.0341 0.0330 1.0000
13.750 0.9252 0.07193 0.06540 0.0328 0.0329 1.0000
14.000 0.9045 0.07745 0.07115 0.0307 0.0329 1.0000
14.250 0.8819 0.08365 0.07759 0.0277 0.0329 1.0000
14.500 0.8576 0.09068 0.08482 0.0238 0.0331 1.0000
14.750 0.8295 0.09918 0.09349 0.0186 0.0332 1.0000
15.000 0.8007 0.10903 0.10350 0.0123 0.0334 1.0000
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