NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il) Reynolds number: 100,000 Max Cl/Cd: 33.64 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652415a05-il-100000.txt Download as CSV file: xf-naca652415a05-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3453 0.11736 0.11281 -0.0504 1.0000 0.1179
-11.250 -0.3718 0.11837 0.11394 -0.0452 1.0000 0.1188
-11.000 -0.3942 0.11478 0.11044 -0.0535 0.9938 0.1246
-10.750 -0.3711 0.10935 0.10497 -0.0551 0.9895 0.1277
-10.500 -0.3446 0.10560 0.10117 -0.0573 0.9856 0.1341
-10.250 -0.3811 0.09869 0.09436 -0.0724 0.9767 0.1411
-10.000 -0.3225 0.09627 0.09182 -0.0670 0.9758 0.1475
-9.750 -0.3832 0.08814 0.08376 -0.0876 0.9634 0.1560
-9.500 -0.3056 0.08704 0.08260 -0.0784 0.9656 0.1689
-9.250 -0.2859 0.08293 0.07846 -0.0814 0.9614 0.1789
-9.000 -0.2950 0.07775 0.07332 -0.0881 0.9527 0.1908
-8.750 -0.3132 0.07326 0.06882 -0.0950 0.9420 0.2021
-8.500 -0.2737 0.07114 0.06667 -0.0926 0.9393 0.2141
-8.250 -0.2727 0.06746 0.06299 -0.0951 0.9322 0.2272
-8.000 -0.3136 0.06496 0.06048 -0.0947 0.9190 0.2383
-7.250 -0.4115 0.04578 0.03874 -0.0881 0.8883 0.0939
-7.000 -0.3909 0.04205 0.03473 -0.0880 0.8853 0.0888
-6.750 -0.3994 0.04078 0.03311 -0.0825 0.8771 0.0859
-6.500 -0.3802 0.03871 0.03062 -0.0814 0.8730 0.0857
-6.250 -0.3520 0.03665 0.02816 -0.0817 0.8704 0.0860
-6.000 -0.3577 0.03623 0.02750 -0.0765 0.8636 0.0854
-5.750 -0.3397 0.03499 0.02598 -0.0750 0.8597 0.0853
-5.500 -0.3101 0.03365 0.02446 -0.0754 0.8569 0.0872
-5.250 -0.2756 0.03251 0.02314 -0.0765 0.8547 0.0913
-5.000 -0.2824 0.03263 0.02317 -0.0711 0.8483 0.0924
-4.750 -0.2679 0.03217 0.02257 -0.0690 0.8447 0.0941
-4.500 -0.2410 0.03124 0.02161 -0.0689 0.8421 0.0971
-4.250 -0.2088 0.03040 0.02089 -0.0699 0.8399 0.1046
-4.000 -0.1996 0.03039 0.02080 -0.0670 0.8360 0.1095
-3.750 -0.2082 0.03049 0.02097 -0.0615 0.8315 0.1123
-3.500 -0.1973 0.03031 0.02086 -0.0592 0.8286 0.1195
-3.250 -0.1774 0.02992 0.02054 -0.0581 0.8259 0.1357
-3.000 -0.1563 0.02851 0.01987 -0.0576 0.8235 0.2361
-2.750 -0.1708 0.02747 0.02085 -0.0495 0.8207 0.6648
-2.500 -0.1765 0.02828 0.02178 -0.0432 0.8182 0.7278
-2.250 -0.1736 0.02901 0.02253 -0.0381 0.8153 0.7716
-2.000 -0.1648 0.02968 0.02319 -0.0339 0.8126 0.8060
-1.750 -0.1575 0.03041 0.02391 -0.0293 0.8109 0.8400
-1.500 -0.1502 0.03120 0.02471 -0.0237 0.8091 0.8815
-1.250 -0.0131 0.03365 0.02684 -0.0374 0.8065 0.9345
-1.000 0.0036 0.03420 0.02731 -0.0379 0.8028 0.9468
-0.750 0.0320 0.03473 0.02774 -0.0400 0.8002 0.9577
-0.500 0.0799 0.03527 0.02815 -0.0455 0.7975 0.9639
-0.250 0.1241 0.03567 0.02842 -0.0499 0.7944 0.9720
0.000 0.1851 0.03598 0.02862 -0.0568 0.7917 0.9766
0.250 0.2267 0.03655 0.02911 -0.0611 0.7890 0.9847
0.500 0.2535 0.03736 0.02989 -0.0642 0.7854 0.9954
0.750 0.2625 0.03793 0.03043 -0.0636 0.7820 1.0000
1.000 0.2421 0.03832 0.03079 -0.0577 0.7796 1.0000
1.250 0.2421 0.03857 0.03099 -0.0544 0.7766 1.0000
1.500 0.2490 0.03898 0.03134 -0.0520 0.7736 1.0000
1.750 0.2078 0.03939 0.03169 -0.0431 0.7719 1.0000
2.000 0.2027 0.04012 0.03235 -0.0397 0.7700 1.0000
2.250 0.2093 0.04096 0.03312 -0.0380 0.7675 1.0000
2.500 0.2240 0.04182 0.03393 -0.0373 0.7645 1.0000
2.750 0.2589 0.04241 0.03447 -0.0385 0.7553 1.0000
3.000 0.2648 0.04338 0.03541 -0.0369 0.7519 1.0000
3.250 0.3054 0.04394 0.03594 -0.0388 0.7441 1.0000
3.500 0.3108 0.04486 0.03684 -0.0369 0.7371 1.0000
3.750 0.3391 0.04552 0.03749 -0.0374 0.7298 1.0000
4.000 0.3560 0.04632 0.03828 -0.0367 0.7210 1.0000
4.250 0.3858 0.04695 0.03892 -0.0374 0.7137 1.0000
4.500 0.4007 0.04777 0.03975 -0.0364 0.7042 1.0000
4.750 0.4387 0.04821 0.04022 -0.0377 0.6970 1.0000
5.000 0.4476 0.04910 0.04114 -0.0362 0.6864 1.0000
5.250 0.4961 0.04924 0.04134 -0.0383 0.6802 1.0000
5.500 0.4996 0.05023 0.04237 -0.0363 0.6685 1.0000
5.750 0.5252 0.05078 0.04297 -0.0362 0.6592 1.0000
6.000 0.5577 0.05101 0.04327 -0.0367 0.6509 1.0000
6.250 0.5713 0.05183 0.04416 -0.0356 0.6394 1.0000
6.500 0.6193 0.05140 0.04385 -0.0371 0.6339 1.0000
6.750 0.6293 0.05225 0.04477 -0.0357 0.6212 1.0000
7.000 0.6493 0.05274 0.04536 -0.0349 0.6100 1.0000
7.250 0.6947 0.05193 0.04470 -0.0358 0.6039 1.0000
7.500 0.7105 0.05239 0.04527 -0.0346 0.5910 1.0000
7.750 0.7702 0.05008 0.04318 -0.0357 0.5862 1.0000
8.000 0.8137 0.04745 0.04074 -0.0349 0.5731 1.0000
8.750 0.9763 0.03204 0.02605 -0.0297 0.5183 1.0000
9.000 0.9893 0.03122 0.02532 -0.0268 0.4791 1.0000
9.250 0.9970 0.02964 0.02225 -0.0206 0.2801 1.0000
9.500 0.9703 0.03324 0.02508 -0.0164 0.1939 1.0000
9.750 0.9520 0.03661 0.02776 -0.0131 0.1366 1.0000
10.000 0.9480 0.03902 0.02986 -0.0108 0.1112 1.0000
10.250 0.9520 0.04087 0.03151 -0.0088 0.0969 1.0000
10.500 0.9642 0.04219 0.03280 -0.0073 0.0870 1.0000
10.750 0.9850 0.04314 0.03365 -0.0059 0.0801 1.0000
11.000 1.0092 0.04407 0.03445 -0.0051 0.0734 1.0000
11.250 1.0476 0.04487 0.03528 -0.0048 0.0687 1.0000
11.500 1.0866 0.04603 0.03653 -0.0048 0.0651 1.0000
11.750 1.1339 0.04766 0.03813 -0.0059 0.0619 1.0000
12.000 1.1724 0.05040 0.04111 -0.0067 0.0593 1.0000
12.250 1.1903 0.05291 0.04395 -0.0059 0.0585 1.0000
12.500 1.2045 0.05586 0.04725 -0.0050 0.0581 1.0000
12.750 1.2132 0.05904 0.05076 -0.0038 0.0581 1.0000
13.000 1.2157 0.06249 0.05454 -0.0023 0.0582 1.0000
13.250 1.2137 0.06616 0.05853 -0.0008 0.0585 1.0000
13.500 1.2080 0.06998 0.06263 0.0006 0.0589 1.0000
13.750 1.1983 0.07399 0.06690 0.0019 0.0592 1.0000
14.000 1.1858 0.07818 0.07134 0.0030 0.0595 1.0000
14.250 1.1716 0.08272 0.07611 0.0037 0.0598 1.0000
14.500 1.1621 0.08785 0.08142 0.0038 0.0602 1.0000
14.750 1.1522 0.09326 0.08703 0.0038 0.0606 1.0000
15.000 1.1211 0.09664 0.09070 0.0037 0.0613 1.0000
15.250 0.8163 0.10959 0.10489 -0.0018 0.0661 1.0000
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Polar data table (+)
Polar graphs
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