NACA 65(2)-415 (naca652415-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-415 (naca652415-il) Reynolds number: 500,000 Max Cl/Cd: 100.41 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652415-il-500000.txt Download as CSV file: xf-naca652415-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6031 0.06174 0.05897 -0.0821 1.0000 0.0226
-12.000 -0.6267 0.05714 0.05427 -0.0831 1.0000 0.0224
-11.750 -0.6514 0.05339 0.05044 -0.0825 1.0000 0.0223
-11.500 -0.6705 0.04968 0.04661 -0.0827 0.9967 0.0221
-11.250 -0.6800 0.04386 0.04046 -0.0870 0.9837 0.0219
-11.000 -0.6844 0.03813 0.03425 -0.0902 0.9718 0.0220
-10.750 -0.6777 0.03388 0.02951 -0.0917 0.9601 0.0224
-10.500 -0.6654 0.03158 0.02679 -0.0918 0.9478 0.0228
-10.250 -0.6573 0.02834 0.02318 -0.0909 0.9356 0.0234
-10.000 -0.6387 0.02695 0.02170 -0.0905 0.9260 0.0241
-9.750 -0.6212 0.02592 0.02058 -0.0895 0.9156 0.0245
-9.500 -0.6027 0.02487 0.01939 -0.0886 0.9071 0.0251
-9.250 -0.5845 0.02367 0.01800 -0.0876 0.8981 0.0256
-9.000 -0.5646 0.02252 0.01666 -0.0867 0.8904 0.0263
-8.750 -0.5442 0.02162 0.01559 -0.0858 0.8821 0.0271
-8.500 -0.5229 0.02101 0.01479 -0.0849 0.8749 0.0277
-8.250 -0.5007 0.01985 0.01346 -0.0843 0.8675 0.0283
-8.000 -0.4765 0.01833 0.01187 -0.0840 0.8618 0.0291
-7.750 -0.4538 0.01755 0.01108 -0.0835 0.8548 0.0298
-7.500 -0.4309 0.01696 0.01043 -0.0829 0.8482 0.0306
-7.250 -0.4077 0.01645 0.00987 -0.0824 0.8418 0.0317
-7.000 -0.3847 0.01592 0.00927 -0.0818 0.8351 0.0327
-6.750 -0.3613 0.01540 0.00866 -0.0812 0.8297 0.0335
-6.500 -0.3379 0.01497 0.00818 -0.0806 0.8234 0.0341
-6.250 -0.3185 0.01407 0.00722 -0.0796 0.8173 0.0352
-6.000 -0.2967 0.01351 0.00662 -0.0789 0.8119 0.0365
-5.750 -0.2733 0.01312 0.00622 -0.0784 0.8057 0.0381
-5.500 -0.2490 0.01277 0.00581 -0.0780 0.8004 0.0400
-5.250 -0.2242 0.01247 0.00544 -0.0777 0.7955 0.0413
-5.000 -0.2012 0.01193 0.00487 -0.0773 0.7900 0.0440
-4.750 -0.1760 0.01160 0.00451 -0.0770 0.7850 0.0474
-4.500 -0.1501 0.01132 0.00417 -0.0769 0.7804 0.0523
-4.250 -0.1249 0.01094 0.00385 -0.0767 0.7751 0.0641
-4.000 -0.1032 0.00998 0.00337 -0.0765 0.7702 0.1733
-3.750 -0.0848 0.00834 0.00276 -0.0764 0.7660 0.4391
-3.500 -0.0591 0.00796 0.00274 -0.0763 0.7614 0.5507
-3.250 -0.0310 0.00792 0.00273 -0.0765 0.7568 0.5845
-3.000 -0.0026 0.00793 0.00272 -0.0766 0.7526 0.6036
-2.750 0.0261 0.00798 0.00271 -0.0768 0.7487 0.6184
-2.500 0.0546 0.00801 0.00274 -0.0770 0.7443 0.6330
-2.250 0.0824 0.00813 0.00290 -0.0769 0.7402 0.6548
-2.000 0.1102 0.00831 0.00309 -0.0767 0.7366 0.6734
-1.750 0.1389 0.00840 0.00313 -0.0769 0.7328 0.6828
-1.500 0.1673 0.00839 0.00313 -0.0771 0.7287 0.6867
-1.250 0.1961 0.00839 0.00311 -0.0774 0.7247 0.6906
-1.000 0.2253 0.00841 0.00307 -0.0778 0.7213 0.6944
-0.750 0.2546 0.00846 0.00304 -0.0782 0.7181 0.6980
-0.500 0.2829 0.00843 0.00306 -0.0784 0.7143 0.7012
-0.250 0.3116 0.00844 0.00307 -0.0787 0.7104 0.7046
0.000 0.3406 0.00847 0.00307 -0.0791 0.7069 0.7086
0.250 0.3700 0.00853 0.00307 -0.0795 0.7039 0.7125
0.500 0.3986 0.00854 0.00311 -0.0798 0.7006 0.7158
0.750 0.4269 0.00855 0.00316 -0.0801 0.6968 0.7193
1.000 0.4556 0.00858 0.00320 -0.0804 0.6933 0.7233
1.250 0.4847 0.00863 0.00324 -0.0808 0.6902 0.7276
1.500 0.5140 0.00871 0.00329 -0.0812 0.6871 0.7313
1.750 0.5419 0.00872 0.00338 -0.0814 0.6837 0.7348
2.000 0.5702 0.00876 0.00347 -0.0816 0.6801 0.7391
2.250 0.5991 0.00882 0.00354 -0.0819 0.6766 0.7438
2.500 0.6279 0.00886 0.00359 -0.0823 0.6732 0.7479
2.750 0.6558 0.00891 0.00370 -0.0824 0.6687 0.7518
3.000 0.6834 0.00892 0.00376 -0.0824 0.6631 0.7563
3.250 0.7120 0.00895 0.00379 -0.0827 0.6580 0.7613
3.500 0.7389 0.00895 0.00385 -0.0825 0.6507 0.7658
3.750 0.7657 0.00892 0.00381 -0.0823 0.6405 0.7705
4.000 0.7910 0.00886 0.00377 -0.0818 0.6266 0.7758
4.250 0.8162 0.00883 0.00377 -0.0813 0.6114 0.7807
4.500 0.8416 0.00885 0.00385 -0.0808 0.5984 0.7855
4.750 0.8675 0.00892 0.00395 -0.0805 0.5855 0.7914
5.000 0.8926 0.00899 0.00404 -0.0801 0.5693 0.7970
5.250 0.9157 0.00912 0.00417 -0.0792 0.5472 0.8024
5.500 0.9371 0.00935 0.00432 -0.0781 0.5104 0.8088
5.750 0.9485 0.01001 0.00466 -0.0752 0.4332 0.8149
6.000 0.9492 0.01130 0.00541 -0.0707 0.3284 0.8224
6.250 0.9500 0.01255 0.00621 -0.0664 0.2372 0.8302
6.500 0.9487 0.01370 0.00698 -0.0617 0.1604 0.8391
6.750 0.9450 0.01480 0.00777 -0.0566 0.0987 0.8484
7.000 0.9463 0.01586 0.00860 -0.0526 0.0596 0.8589
7.250 0.9543 0.01658 0.00931 -0.0496 0.0466 0.8688
7.500 0.9631 0.01731 0.01006 -0.0468 0.0405 0.8798
7.750 0.9748 0.01791 0.01074 -0.0445 0.0372 0.8921
8.000 0.9811 0.01872 0.01160 -0.0414 0.0343 0.9072
8.250 0.9882 0.01940 0.01240 -0.0384 0.0326 0.9263
8.500 0.9981 0.01999 0.01310 -0.0360 0.0311 0.9585
8.750 1.0154 0.02092 0.01405 -0.0357 0.0292 1.0000
9.000 1.0239 0.02228 0.01543 -0.0342 0.0277 1.0000
9.250 1.0368 0.02335 0.01655 -0.0331 0.0268 1.0000
9.500 1.0505 0.02436 0.01761 -0.0321 0.0259 1.0000
9.750 1.0636 0.02543 0.01871 -0.0310 0.0251 1.0000
10.000 1.0757 0.02658 0.01990 -0.0299 0.0244 1.0000
10.250 1.0873 0.02778 0.02112 -0.0288 0.0236 1.0000
10.500 1.0965 0.02922 0.02257 -0.0275 0.0229 1.0000
10.750 1.1044 0.03091 0.02430 -0.0260 0.0224 1.0000
11.000 1.1179 0.03215 0.02560 -0.0250 0.0220 1.0000
11.250 1.1323 0.03329 0.02682 -0.0242 0.0216 1.0000
11.500 1.1468 0.03446 0.02806 -0.0235 0.0211 1.0000
11.750 1.1613 0.03567 0.02934 -0.0227 0.0206 1.0000
12.000 1.1754 0.03690 0.03062 -0.0220 0.0201 1.0000
12.250 1.1888 0.03818 0.03195 -0.0213 0.0196 1.0000
12.500 1.2028 0.03952 0.03335 -0.0207 0.0192 1.0000
12.750 1.2170 0.04091 0.03479 -0.0201 0.0189 1.0000
13.000 1.2321 0.04236 0.03627 -0.0195 0.0185 1.0000
13.250 1.2528 0.04400 0.03797 -0.0191 0.0182 1.0000
13.500 1.2697 0.04623 0.04037 -0.0186 0.0178 1.0000
13.750 1.2768 0.04823 0.04253 -0.0178 0.0177 1.0000
14.000 1.2831 0.05050 0.04499 -0.0170 0.0176 1.0000
14.250 1.2859 0.05297 0.04764 -0.0162 0.0174 1.0000
14.500 1.2873 0.05573 0.05059 -0.0155 0.0173 1.0000
14.750 1.2854 0.05880 0.05388 -0.0149 0.0172 1.0000
15.000 1.2816 0.06201 0.05728 -0.0146 0.0170 1.0000
15.250 1.2748 0.06582 0.06130 -0.0144 0.0168 1.0000
15.500 1.2665 0.06985 0.06554 -0.0145 0.0167 1.0000
15.750 1.2551 0.07439 0.07029 -0.0150 0.0166 1.0000
16.000 1.2404 0.07963 0.07575 -0.0159 0.0165 1.0000
16.250 1.2221 0.08568 0.08204 -0.0174 0.0165 1.0000
16.500 1.2015 0.09234 0.08893 -0.0197 0.0166 1.0000
16.750 1.1783 0.09984 0.09665 -0.0227 0.0167 1.0000
17.000 1.1536 0.10811 0.10514 -0.0268 0.0168 1.0000
17.250 1.1263 0.11750 0.11474 -0.0320 0.0169 1.0000
17.500 1.0974 0.12803 0.12547 -0.0384 0.0170 1.0000
17.750 1.0663 0.14011 0.13773 -0.0462 0.0173 1.0000
18.000 1.0310 0.15454 0.15231 -0.0558 0.0176 1.0000
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