NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.09 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652415a05-il-1000000-n5.txt Download as CSV file: xf-naca652415a05-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415 a=0.5
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0659 0.04373 0.04030 -0.0840 0.9079 0.0085
-16.500 -1.0734 0.04066 0.03707 -0.0844 0.8886 0.0086
-16.250 -1.0799 0.03786 0.03408 -0.0845 0.8732 0.0086
-16.000 -1.0810 0.03567 0.03175 -0.0843 0.8602 0.0087
-15.750 -1.0776 0.03394 0.02993 -0.0839 0.8491 0.0089
-15.500 -1.0758 0.03214 0.02800 -0.0833 0.8395 0.0091
-15.250 -1.0708 0.03068 0.02643 -0.0825 0.8303 0.0092
-15.000 -1.0679 0.02911 0.02474 -0.0815 0.8225 0.0093
-14.750 -1.0600 0.02796 0.02349 -0.0805 0.8146 0.0095
-14.500 -1.0553 0.02664 0.02204 -0.0791 0.8074 0.0096
-14.250 -1.0454 0.02571 0.02102 -0.0779 0.7998 0.0098
-14.000 -1.0360 0.02479 0.01998 -0.0765 0.7929 0.0100
-13.750 -1.0282 0.02377 0.01886 -0.0748 0.7862 0.0101
-13.500 -1.0174 0.02299 0.01796 -0.0732 0.7797 0.0103
-13.250 -1.0069 0.02220 0.01707 -0.0714 0.7742 0.0104
-13.000 -0.9963 0.02146 0.01622 -0.0694 0.7684 0.0106
-12.750 -0.9854 0.02079 0.01547 -0.0673 0.7628 0.0108
-12.500 -0.9704 0.02027 0.01488 -0.0658 0.7580 0.0111
-12.250 -0.9526 0.01972 0.01427 -0.0647 0.7527 0.0113
-12.000 -0.9334 0.01925 0.01374 -0.0638 0.7474 0.0116
-11.750 -0.9133 0.01879 0.01321 -0.0629 0.7428 0.0118
-11.500 -0.8925 0.01834 0.01269 -0.0622 0.7381 0.0122
-11.250 -0.8714 0.01789 0.01216 -0.0615 0.7335 0.0125
-10.750 -0.8275 0.01703 0.01114 -0.0603 0.7256 0.0131
-10.500 -0.8056 0.01654 0.01059 -0.0597 0.7216 0.0134
-10.250 -0.7833 0.01608 0.01007 -0.0591 0.7175 0.0138
-9.750 -0.7357 0.01539 0.00930 -0.0584 0.7101 0.0145
-9.500 -0.7114 0.01505 0.00891 -0.0580 0.7062 0.0149
-9.250 -0.6871 0.01471 0.00851 -0.0577 0.7021 0.0153
-9.000 -0.6625 0.01439 0.00812 -0.0574 0.6984 0.0157
-8.750 -0.6375 0.01408 0.00776 -0.0572 0.6953 0.0160
-8.500 -0.6121 0.01379 0.00742 -0.0570 0.6921 0.0163
-8.250 -0.5881 0.01335 0.00695 -0.0566 0.6887 0.0169
-8.000 -0.5629 0.01304 0.00659 -0.0564 0.6854 0.0174
-7.750 -0.5373 0.01277 0.00629 -0.0562 0.6822 0.0178
-7.500 -0.5113 0.01251 0.00600 -0.0561 0.6794 0.0182
-7.250 -0.4852 0.01225 0.00571 -0.0560 0.6765 0.0188
-7.000 -0.4588 0.01202 0.00544 -0.0559 0.6733 0.0193
-6.750 -0.4326 0.01177 0.00515 -0.0558 0.6700 0.0197
-6.500 -0.4061 0.01156 0.00488 -0.0558 0.6668 0.0200
-6.250 -0.3804 0.01122 0.00451 -0.0556 0.6641 0.0207
-6.000 -0.3537 0.01097 0.00426 -0.0556 0.6616 0.0214
-5.750 -0.3267 0.01077 0.00405 -0.0556 0.6590 0.0221
-5.500 -0.2996 0.01057 0.00382 -0.0556 0.6563 0.0227
-5.250 -0.2725 0.01039 0.00361 -0.0557 0.6536 0.0234
-5.000 -0.2453 0.01022 0.00340 -0.0557 0.6511 0.0240
-4.750 -0.2179 0.01005 0.00321 -0.0558 0.6488 0.0246
-4.500 -0.1906 0.00983 0.00299 -0.0558 0.6466 0.0260
-4.250 -0.1630 0.00967 0.00282 -0.0560 0.6441 0.0270
-4.000 -0.1352 0.00952 0.00267 -0.0561 0.6415 0.0282
-3.750 -0.1073 0.00940 0.00252 -0.0562 0.6390 0.0294
-3.500 -0.0796 0.00926 0.00237 -0.0564 0.6368 0.0312
-3.250 -0.0518 0.00914 0.00224 -0.0565 0.6346 0.0336
-3.000 -0.0237 0.00902 0.00213 -0.0567 0.6328 0.0360
-2.750 0.0043 0.00888 0.00201 -0.0569 0.6309 0.0417
-2.500 0.0323 0.00874 0.00191 -0.0571 0.6287 0.0523
-2.250 0.0597 0.00852 0.00180 -0.0572 0.6264 0.0802
-2.000 0.0867 0.00825 0.00169 -0.0573 0.6242 0.1292
-1.750 0.1133 0.00792 0.00158 -0.0574 0.6222 0.1998
-1.500 0.1386 0.00743 0.00144 -0.0574 0.6203 0.3113
-1.250 0.1631 0.00685 0.00131 -0.0572 0.6183 0.4499
-1.000 0.1891 0.00648 0.00128 -0.0572 0.6167 0.5520
-0.750 0.2164 0.00629 0.00129 -0.0573 0.6148 0.6104
-0.500 0.2443 0.00620 0.00132 -0.0574 0.6128 0.6495
-0.250 0.2729 0.00617 0.00133 -0.0576 0.6110 0.6658
0.000 0.3016 0.00616 0.00134 -0.0579 0.6091 0.6781
0.250 0.3306 0.00618 0.00135 -0.0583 0.6071 0.6851
0.500 0.3594 0.00619 0.00136 -0.0586 0.6051 0.6912
0.750 0.3882 0.00622 0.00139 -0.0589 0.6031 0.6979
1.000 0.4173 0.00624 0.00142 -0.0592 0.6016 0.7044
1.250 0.4462 0.00623 0.00145 -0.0596 0.6000 0.7114
1.500 0.4753 0.00625 0.00149 -0.0600 0.5980 0.7180
1.750 0.5041 0.00626 0.00153 -0.0603 0.5961 0.7243
2.000 0.5329 0.00628 0.00157 -0.0606 0.5941 0.7317
2.250 0.5616 0.00631 0.00163 -0.0610 0.5920 0.7386
2.500 0.5902 0.00634 0.00168 -0.0612 0.5899 0.7458
2.750 0.6187 0.00640 0.00174 -0.0615 0.5877 0.7527
3.000 0.6473 0.00641 0.00181 -0.0618 0.5850 0.7597
3.250 0.6760 0.00642 0.00187 -0.0622 0.5807 0.7676
3.500 0.7040 0.00646 0.00193 -0.0623 0.5746 0.7749
3.750 0.7320 0.00650 0.00200 -0.0626 0.5685 0.7828
4.000 0.7602 0.00654 0.00208 -0.0628 0.5624 0.7900
4.250 0.7876 0.00660 0.00216 -0.0629 0.5534 0.7983
4.500 0.8137 0.00672 0.00224 -0.0627 0.5301 0.8064
4.750 0.8334 0.00723 0.00248 -0.0616 0.4659 0.8154
5.000 0.8433 0.00835 0.00312 -0.0589 0.3623 0.8252
5.250 0.8560 0.00921 0.00368 -0.0567 0.2934 0.8358
5.500 0.8678 0.00998 0.00421 -0.0543 0.2349 0.8467
5.750 0.8801 0.01064 0.00469 -0.0520 0.1900 0.8580
6.250 0.8956 0.01186 0.00566 -0.0455 0.1174 0.8870
6.500 0.8975 0.01248 0.00623 -0.0412 0.0909 0.9071
6.750 0.9042 0.01306 0.00679 -0.0380 0.0716 0.9312
7.000 0.9228 0.01373 0.00743 -0.0374 0.0534 0.9609
7.250 0.9493 0.01447 0.00811 -0.0387 0.0389 1.0000
7.500 0.9624 0.01512 0.00872 -0.0370 0.0314 1.0000
7.750 0.9764 0.01577 0.00934 -0.0356 0.0265 1.0000
8.000 0.9918 0.01636 0.00994 -0.0343 0.0240 1.0000
8.250 1.0063 0.01704 0.01061 -0.0330 0.0214 1.0000
8.500 1.0217 0.01769 0.01126 -0.0319 0.0197 1.0000
8.750 1.0362 0.01840 0.01198 -0.0307 0.0181 1.0000
9.000 1.0512 0.01911 0.01270 -0.0296 0.0171 1.0000
9.250 1.0662 0.01983 0.01344 -0.0285 0.0164 1.0000
9.500 1.0804 0.02062 0.01424 -0.0274 0.0153 1.0000
9.750 1.0942 0.02145 0.01509 -0.0263 0.0146 1.0000
10.000 1.1076 0.02232 0.01598 -0.0252 0.0140 1.0000
10.250 1.1219 0.02316 0.01684 -0.0243 0.0136 1.0000
10.500 1.1358 0.02402 0.01774 -0.0233 0.0130 1.0000
10.750 1.1490 0.02495 0.01869 -0.0224 0.0126 1.0000
11.000 1.1622 0.02589 0.01966 -0.0214 0.0123 1.0000
11.250 1.1743 0.02693 0.02072 -0.0205 0.0119 1.0000
11.500 1.1858 0.02803 0.02185 -0.0195 0.0116 1.0000
11.750 1.1960 0.02923 0.02308 -0.0184 0.0112 1.0000
12.000 1.2076 0.03036 0.02426 -0.0175 0.0111 1.0000
12.250 1.2192 0.03152 0.02546 -0.0167 0.0110 1.0000
12.500 1.2322 0.03260 0.02658 -0.0161 0.0107 1.0000
12.750 1.2436 0.03381 0.02784 -0.0153 0.0105 1.0000
13.000 1.2537 0.03515 0.02922 -0.0146 0.0102 1.0000
13.250 1.2644 0.03648 0.03060 -0.0139 0.0101 1.0000
13.500 1.2745 0.03789 0.03206 -0.0132 0.0101 1.0000
13.750 1.2851 0.03926 0.03347 -0.0127 0.0098 1.0000
14.000 1.2934 0.04087 0.03513 -0.0120 0.0098 1.0000
14.250 1.3028 0.04240 0.03671 -0.0115 0.0096 1.0000
14.500 1.3113 0.04405 0.03841 -0.0110 0.0094 1.0000
14.750 1.3198 0.04572 0.04013 -0.0105 0.0092 1.0000
15.000 1.3268 0.04756 0.04204 -0.0101 0.0092 1.0000
15.250 1.3326 0.04956 0.04408 -0.0097 0.0090 1.0000
15.500 1.3381 0.05164 0.04623 -0.0093 0.0089 1.0000
15.750 1.3423 0.05389 0.04854 -0.0090 0.0088 1.0000
16.000 1.3448 0.05639 0.05112 -0.0088 0.0087 1.0000
16.250 1.3486 0.05876 0.05357 -0.0086 0.0086 1.0000
16.500 1.3547 0.06096 0.05584 -0.0087 0.0086 1.0000
16.750 1.3595 0.06333 0.05829 -0.0087 0.0085 1.0000
17.000 1.3625 0.06596 0.06101 -0.0089 0.0085 1.0000
17.250 1.3666 0.06852 0.06364 -0.0091 0.0085 1.0000
17.500 1.3688 0.07133 0.06653 -0.0094 0.0084 1.0000
17.750 1.3716 0.07414 0.06943 -0.0098 0.0083 1.0000
18.000 1.3726 0.07724 0.07262 -0.0104 0.0082 1.0000
18.250 1.3760 0.08008 0.07553 -0.0110 0.0081 1.0000
18.500 1.3741 0.08371 0.07926 -0.0119 0.0081 1.0000
18.750 1.3732 0.08724 0.08289 -0.0128 0.0080 1.0000
19.000 1.3720 0.09090 0.08664 -0.0139 0.0080 1.0000
19.250 1.3704 0.09469 0.09054 -0.0151 0.0079 1.0000
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Polar data table (+)
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