NACA 63(2)-615 (naca632615-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(2)-615 (naca632615-il) Reynolds number: 200,000 Max Cl/Cd: 81.65 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca632615-il-200000.txt Download as CSV file: xf-naca632615-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)-615
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3764 0.09325 0.08982 -0.0568 1.0000 0.0798
-10.250 -0.5935 0.05839 0.05455 -0.0806 0.9889 0.0460
-10.000 -0.5923 0.05178 0.04758 -0.0880 0.9780 0.0456
-9.750 -0.5822 0.04586 0.04122 -0.0937 0.9707 0.0453
-9.500 -0.5723 0.04109 0.03599 -0.0963 0.9610 0.0452
-9.250 -0.5479 0.03637 0.03073 -0.1002 0.9568 0.0452
-9.000 -0.5284 0.03322 0.02711 -0.1013 0.9483 0.0458
-8.750 -0.4970 0.03023 0.02360 -0.1041 0.9443 0.0475
-8.500 -0.4601 0.02825 0.02161 -0.1071 0.9419 0.0498
-8.250 -0.4335 0.02676 0.01995 -0.1076 0.9345 0.0515
-8.000 -0.4002 0.02517 0.01809 -0.1092 0.9296 0.0537
-7.750 -0.3649 0.02341 0.01611 -0.1112 0.9261 0.0566
-7.500 -0.3388 0.02239 0.01510 -0.1113 0.9185 0.0593
-7.250 -0.3076 0.02138 0.01400 -0.1121 0.9127 0.0622
-7.000 -0.2736 0.02036 0.01281 -0.1133 0.9086 0.0659
-6.750 -0.2527 0.01945 0.01198 -0.1124 0.8991 0.0692
-6.500 -0.2225 0.01872 0.01120 -0.1129 0.8936 0.0736
-6.250 -0.1991 0.01802 0.01046 -0.1123 0.8855 0.0779
-6.000 -0.1730 0.01728 0.00975 -0.1123 0.8785 0.0835
-5.750 -0.1468 0.01668 0.00911 -0.1122 0.8719 0.0903
-5.500 -0.1225 0.01606 0.00852 -0.1120 0.8639 0.0999
-5.250 -0.0940 0.01531 0.00779 -0.1125 0.8585 0.1177
-5.000 -0.0711 0.01424 0.00713 -0.1128 0.8498 0.1796
-4.750 -0.0440 0.01277 0.00661 -0.1142 0.8437 0.3924
-4.500 -0.0165 0.01266 0.00666 -0.1142 0.8368 0.4662
-4.250 0.0115 0.01269 0.00667 -0.1141 0.8298 0.5034
-4.000 0.0413 0.01274 0.00666 -0.1141 0.8248 0.5300
-3.750 0.0674 0.01287 0.00677 -0.1136 0.8168 0.5508
-3.500 0.0960 0.01297 0.00679 -0.1134 0.8107 0.5703
-3.250 0.1238 0.01314 0.00692 -0.1131 0.8046 0.5895
-3.000 0.1503 0.01334 0.00710 -0.1125 0.7975 0.6076
-2.750 0.1781 0.01347 0.00721 -0.1119 0.7923 0.6217
-2.500 0.2038 0.01362 0.00736 -0.1112 0.7851 0.6328
-2.250 0.2314 0.01371 0.00740 -0.1109 0.7788 0.6454
-2.000 0.2601 0.01380 0.00742 -0.1107 0.7741 0.6557
-1.750 0.2860 0.01384 0.00747 -0.1103 0.7663 0.6636
-1.500 0.3143 0.01386 0.00743 -0.1102 0.7606 0.6714
-1.250 0.3429 0.01388 0.00739 -0.1103 0.7550 0.6794
-1.000 0.3691 0.01394 0.00746 -0.1099 0.7482 0.6862
-0.750 0.3995 0.01391 0.00733 -0.1104 0.7429 0.6948
-0.500 0.4255 0.01398 0.00743 -0.1099 0.7366 0.7006
-0.250 0.4537 0.01401 0.00743 -0.1101 0.7303 0.7087
0.000 0.4827 0.01401 0.00738 -0.1101 0.7256 0.7151
0.250 0.5089 0.01410 0.00750 -0.1099 0.7189 0.7220
0.500 0.5376 0.01411 0.00749 -0.1101 0.7129 0.7298
0.750 0.5661 0.01415 0.00749 -0.1100 0.7084 0.7361
1.000 0.5934 0.01425 0.00762 -0.1102 0.7014 0.7447
1.250 0.6197 0.01428 0.00768 -0.1097 0.6957 0.7507
1.500 0.6496 0.01434 0.00768 -0.1100 0.6913 0.7588
1.750 0.6743 0.01445 0.00789 -0.1095 0.6841 0.7656
2.000 0.7020 0.01450 0.00793 -0.1094 0.6786 0.7733
2.250 0.7304 0.01458 0.00800 -0.1095 0.6737 0.7812
2.500 0.7549 0.01469 0.00822 -0.1089 0.6667 0.7889
2.750 0.7837 0.01473 0.00824 -0.1090 0.6614 0.7971
3.000 0.8092 0.01485 0.00841 -0.1085 0.6556 0.8050
3.250 0.8350 0.01495 0.00858 -0.1082 0.6490 0.8138
3.500 0.8626 0.01499 0.00862 -0.1080 0.6439 0.8221
3.750 0.8870 0.01513 0.00885 -0.1074 0.6373 0.8309
4.000 0.9126 0.01520 0.00898 -0.1069 0.6309 0.8404
4.250 0.9395 0.01523 0.00901 -0.1065 0.6257 0.8491
4.500 0.9625 0.01534 0.00924 -0.1057 0.6173 0.8598
4.750 0.9874 0.01528 0.00918 -0.1048 0.6108 0.8693
5.000 1.0077 0.01534 0.00936 -0.1033 0.6020 0.8802
5.250 1.0336 0.01528 0.00929 -0.1027 0.5947 0.8918
5.500 1.0523 0.01530 0.00944 -0.1008 0.5855 0.9050
5.750 1.0752 0.01517 0.00928 -0.0995 0.5775 0.9189
6.000 1.0904 0.01508 0.00934 -0.0969 0.5671 0.9365
6.250 1.1103 0.01491 0.00922 -0.0952 0.5575 0.9597
6.500 1.1419 0.01475 0.00909 -0.0961 0.5427 1.0000
6.750 1.1706 0.01477 0.00913 -0.0967 0.5251 1.0000
7.000 1.1987 0.01490 0.00928 -0.0972 0.5087 1.0000
7.250 1.2258 0.01509 0.00951 -0.0975 0.4927 1.0000
7.500 1.2509 0.01532 0.00977 -0.0974 0.4745 1.0000
7.750 1.2736 0.01560 0.01005 -0.0968 0.4535 1.0000
8.000 1.2934 0.01597 0.01041 -0.0958 0.4283 1.0000
8.250 1.3093 0.01648 0.01084 -0.0941 0.3965 1.0000
8.500 1.3189 0.01723 0.01142 -0.0915 0.3566 1.0000
8.750 1.3194 0.01827 0.01221 -0.0875 0.3121 1.0000
9.000 1.3148 0.01969 0.01336 -0.0832 0.2663 1.0000
9.250 1.3077 0.02146 0.01484 -0.0791 0.2216 1.0000
9.500 1.2996 0.02352 0.01665 -0.0754 0.1803 1.0000
9.750 1.2911 0.02586 0.01874 -0.0721 0.1437 1.0000
10.000 1.2835 0.02837 0.02103 -0.0694 0.1153 1.0000
10.250 1.2795 0.03082 0.02336 -0.0672 0.0963 1.0000
10.500 1.2777 0.03321 0.02569 -0.0654 0.0847 1.0000
10.750 1.2748 0.03580 0.02821 -0.0637 0.0771 1.0000
11.000 1.2804 0.03776 0.03024 -0.0627 0.0705 1.0000
11.250 1.2783 0.04045 0.03288 -0.0614 0.0661 1.0000
11.500 1.2855 0.04237 0.03492 -0.0605 0.0618 1.0000
11.750 1.2889 0.04468 0.03723 -0.0597 0.0584 1.0000
12.000 1.2916 0.04712 0.03968 -0.0588 0.0554 1.0000
12.250 1.2990 0.04917 0.04182 -0.0581 0.0524 1.0000
12.500 1.3048 0.05140 0.04407 -0.0576 0.0497 1.0000
12.750 1.3113 0.05364 0.04628 -0.0568 0.0472 1.0000
13.000 1.3201 0.05567 0.04845 -0.0563 0.0449 1.0000
13.250 1.3293 0.05771 0.05053 -0.0558 0.0429 1.0000
13.500 1.3411 0.05951 0.05226 -0.0551 0.0410 1.0000
13.750 1.3547 0.06132 0.05417 -0.0543 0.0394 1.0000
14.000 1.3646 0.06344 0.05643 -0.0539 0.0379 1.0000
14.250 1.3740 0.06560 0.05869 -0.0536 0.0365 1.0000
14.500 1.3855 0.06756 0.06065 -0.0534 0.0351 1.0000
14.750 1.4068 0.06913 0.06222 -0.0525 0.0337 1.0000
15.000 1.4108 0.07204 0.06537 -0.0524 0.0331 1.0000
15.250 1.4149 0.07508 0.06864 -0.0523 0.0325 1.0000
15.500 1.4181 0.07831 0.07209 -0.0523 0.0319 1.0000
15.750 1.4198 0.08177 0.07577 -0.0525 0.0314 1.0000
16.000 1.4197 0.08547 0.07967 -0.0529 0.0310 1.0000
16.250 1.4178 0.08944 0.08385 -0.0535 0.0306 1.0000
16.500 1.4147 0.09358 0.08817 -0.0544 0.0303 1.0000
16.750 1.4111 0.09783 0.09260 -0.0555 0.0300 1.0000
17.000 1.4058 0.10232 0.09726 -0.0569 0.0296 1.0000
17.250 1.3980 0.10728 0.10239 -0.0587 0.0294 1.0000
17.500 1.3905 0.11230 0.10757 -0.0607 0.0291 1.0000
17.750 1.3784 0.11818 0.11365 -0.0633 0.0290 1.0000
18.000 1.3619 0.12496 0.12067 -0.0669 0.0290 1.0000
18.250 1.3411 0.13280 0.12875 -0.0715 0.0290 1.0000
18.500 1.1334 0.19271 0.18979 -0.1128 0.0350 1.0000
18.750 1.1432 0.19445 0.19154 -0.1138 0.0346 1.0000
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