NACA 65(3)-618 (naca653618-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(3)-618 (naca653618-il) Reynolds number: 50,000 Max Cl/Cd: 15.26 at α=12.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca653618-il-50000-n5.txt Download as CSV file: xf-naca653618-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(3)-618
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4238 0.11919 0.11226 -0.0624 1.0000 0.0681
-12.250 -0.4358 0.11584 0.10900 -0.0619 0.9996 0.0678
-12.000 -0.4365 0.10835 0.10149 -0.0677 0.9943 0.0674
-11.750 -0.4474 0.09974 0.09283 -0.0745 0.9884 0.0671
-11.500 -0.4667 0.09105 0.08406 -0.0817 0.9821 0.0666
-11.250 -0.4911 0.08339 0.07625 -0.0879 0.9741 0.0661
-11.000 -0.5157 0.07728 0.06996 -0.0922 0.9649 0.0658
-10.750 -0.5366 0.07232 0.06474 -0.0953 0.9563 0.0656
-10.500 -0.5568 0.06878 0.06097 -0.0957 0.9458 0.0656
-10.250 -0.5735 0.06589 0.05783 -0.0947 0.9352 0.0658
-10.000 -0.5783 0.06235 0.05390 -0.0952 0.9273 0.0663
-9.750 -0.5863 0.05989 0.05114 -0.0931 0.9176 0.0667
-9.500 -0.5805 0.05692 0.04776 -0.0930 0.9112 0.0671
-9.250 -0.5777 0.05458 0.04504 -0.0914 0.9037 0.0675
-9.000 -0.5695 0.05232 0.04237 -0.0903 0.8968 0.0681
-8.750 -0.5453 0.05007 0.03994 -0.0914 0.8929 0.0699
-8.500 -0.5335 0.04875 0.03850 -0.0899 0.8862 0.0715
-8.250 -0.5164 0.04729 0.03684 -0.0891 0.8802 0.0734
-8.000 -0.4881 0.04553 0.03477 -0.0899 0.8765 0.0754
-7.750 -0.4519 0.04381 0.03272 -0.0915 0.8740 0.0774
-7.500 -0.4460 0.04324 0.03194 -0.0880 0.8658 0.0788
-7.250 -0.4154 0.04219 0.03097 -0.0884 0.8620 0.0821
-7.000 -0.3790 0.04129 0.02998 -0.0895 0.8592 0.0866
-6.500 -0.3343 0.04026 0.02880 -0.0870 0.8494 0.0938
-6.250 -0.3173 0.03974 0.02825 -0.0856 0.8442 0.0987
-6.000 -0.2936 0.03901 0.02745 -0.0853 0.8407 0.1059
-5.750 -0.2902 0.03860 0.02707 -0.0821 0.8347 0.1112
-5.500 -0.2887 0.03828 0.02668 -0.0786 0.8277 0.1176
-5.250 -0.2736 0.03734 0.02583 -0.0776 0.8235 0.1317
-5.000 -0.2593 0.03615 0.02485 -0.0768 0.8200 0.1569
-4.750 -0.2725 0.03586 0.02475 -0.0715 0.8115 0.1784
-4.500 -0.2689 0.03385 0.02380 -0.0700 0.8071 0.3140
-4.250 -0.2532 0.03472 0.02576 -0.0649 0.8041 0.5332
-4.000 -0.2512 0.03527 0.02614 -0.0613 0.7974 0.5779
-3.750 -0.2397 0.03637 0.02715 -0.0575 0.7923 0.6176
-3.500 -0.2269 0.03829 0.02905 -0.0517 0.7887 0.6677
-3.250 -0.2079 0.04066 0.03140 -0.0446 0.7862 0.7078
-3.000 -0.2116 0.04162 0.03231 -0.0386 0.7797 0.7260
-2.750 -0.2006 0.04187 0.03240 -0.0360 0.7749 0.7404
-2.500 -0.1769 0.04210 0.03245 -0.0350 0.7718 0.7476
-2.250 -0.1533 0.04196 0.03209 -0.0350 0.7692 0.7566
-2.000 -0.1477 0.04221 0.03225 -0.0323 0.7641 0.7633
-1.750 -0.1377 0.04237 0.03230 -0.0303 0.7590 0.7700
-1.500 -0.1176 0.04225 0.03200 -0.0304 0.7553 0.7773
-1.250 -0.0920 0.04230 0.03191 -0.0304 0.7527 0.7818
-1.000 -0.0661 0.04233 0.03178 -0.0307 0.7503 0.7872
-0.750 -0.0682 0.04272 0.03211 -0.0281 0.7437 0.7944
-0.500 -0.0497 0.04290 0.03219 -0.0273 0.7396 0.7988
-0.250 -0.0257 0.04302 0.03220 -0.0274 0.7366 0.8038
0.000 0.0023 0.04309 0.03215 -0.0284 0.7343 0.8092
0.250 0.0092 0.04358 0.03258 -0.0267 0.7290 0.8146
0.500 0.0232 0.04394 0.03290 -0.0256 0.7242 0.8196
0.750 0.0462 0.04420 0.03307 -0.0259 0.7208 0.8251
1.000 0.0742 0.04442 0.03320 -0.0270 0.7181 0.8303
1.250 0.0948 0.04477 0.03350 -0.0267 0.7147 0.8349
1.500 0.1008 0.04544 0.03416 -0.0250 0.7087 0.8410
1.750 0.1226 0.04586 0.03454 -0.0254 0.7048 0.8470
2.000 0.1479 0.04615 0.03480 -0.0256 0.7017 0.8520
2.250 0.1783 0.04640 0.03501 -0.0266 0.6993 0.8574
2.500 0.1799 0.04735 0.03597 -0.0248 0.6922 0.8643
2.750 0.1986 0.04782 0.03645 -0.0243 0.6878 0.8705
3.000 0.2262 0.04819 0.03680 -0.0251 0.6845 0.8774
3.250 0.2570 0.04845 0.03707 -0.0261 0.6820 0.8834
3.500 0.2557 0.04954 0.03821 -0.0239 0.6740 0.8916
3.750 0.2790 0.05000 0.03869 -0.0242 0.6694 0.8994
4.000 0.3091 0.05031 0.03902 -0.0251 0.6662 0.9078
4.250 0.3174 0.05126 0.04004 -0.0240 0.6593 0.9175
4.500 0.3386 0.05188 0.04072 -0.0244 0.6536 0.9275
4.750 0.3705 0.05229 0.04118 -0.0258 0.6500 0.9380
5.250 0.4150 0.05408 0.04317 -0.0282 0.6366 0.9642
5.500 0.4532 0.05439 0.04356 -0.0309 0.6325 0.9888
5.750 0.4623 0.05569 0.04492 -0.0309 0.6235 1.0000
6.000 0.4916 0.05638 0.04567 -0.0326 0.6180 1.0000
6.250 0.5298 0.05676 0.04612 -0.0349 0.6146 1.0000
6.500 0.5346 0.05845 0.04787 -0.0346 0.6036 1.0000
6.750 0.5706 0.05885 0.04836 -0.0365 0.5991 1.0000
7.000 0.5800 0.06042 0.05000 -0.0366 0.5887 1.0000
7.250 0.6133 0.06086 0.05053 -0.0381 0.5833 1.0000
7.500 0.6252 0.06231 0.05209 -0.0382 0.5730 1.0000
7.750 0.6573 0.06269 0.05257 -0.0394 0.5670 1.0000
8.000 0.6689 0.06414 0.05411 -0.0393 0.5560 1.0000
8.250 0.7026 0.06428 0.05439 -0.0404 0.5501 1.0000
8.500 0.7124 0.06577 0.05599 -0.0401 0.5380 1.0000
8.750 0.7500 0.06543 0.05580 -0.0410 0.5327 1.0000
9.000 0.7577 0.06699 0.05748 -0.0405 0.5195 1.0000
9.250 0.7718 0.06813 0.05876 -0.0403 0.5076 1.0000
9.500 0.8075 0.06751 0.05832 -0.0407 0.5010 1.0000
10.000 0.8313 0.06983 0.06094 -0.0398 0.4741 1.0000
10.250 0.8504 0.07027 0.06155 -0.0394 0.4618 1.0000
10.500 0.8860 0.06884 0.06035 -0.0390 0.4530 1.0000
10.750 0.9024 0.06912 0.06082 -0.0383 0.4379 1.0000
11.500 0.9585 0.06739 0.05958 -0.0345 0.3769 1.0000
11.750 0.9847 0.06542 0.05759 -0.0327 0.3398 1.0000
12.000 0.9997 0.06563 0.05767 -0.0315 0.2983 1.0000
12.250 1.0120 0.06633 0.05808 -0.0302 0.2521 1.0000
12.500 1.0136 0.06861 0.06002 -0.0293 0.2091 1.0000
12.750 1.0097 0.07189 0.06300 -0.0289 0.1724 1.0000
13.000 1.0051 0.07547 0.06631 -0.0287 0.1442 1.0000
13.250 1.0018 0.07907 0.06969 -0.0287 0.1236 1.0000
13.500 1.0007 0.08249 0.07296 -0.0288 0.1089 1.0000
13.750 1.0032 0.08554 0.07594 -0.0289 0.0977 1.0000
14.000 1.0082 0.08830 0.07869 -0.0289 0.0890 1.0000
14.250 1.0138 0.09093 0.08123 -0.0290 0.0828 1.0000
14.500 1.0237 0.09312 0.08355 -0.0290 0.0768 1.0000
14.750 1.0334 0.09519 0.08553 -0.0290 0.0725 1.0000
15.000 1.0458 0.09717 0.08773 -0.0289 0.0681 1.0000
15.250 1.0587 0.09895 0.08957 -0.0289 0.0647 1.0000
15.500 1.0750 0.10038 0.09107 -0.0285 0.0619 1.0000
15.750 1.0871 0.10261 0.09355 -0.0287 0.0591 1.0000
16.000 1.0992 0.10472 0.09579 -0.0289 0.0568 1.0000
16.250 1.1166 0.10604 0.09707 -0.0288 0.0547 1.0000
16.500 1.1205 0.10971 0.10112 -0.0296 0.0535 1.0000
16.750 1.1207 0.11390 0.10563 -0.0308 0.0526 1.0000
17.000 1.1168 0.11872 0.11073 -0.0326 0.0517 1.0000
17.250 1.1096 0.12412 0.11640 -0.0349 0.0510 1.0000
17.500 1.0989 0.13024 0.12277 -0.0379 0.0504 1.0000
17.750 1.0827 0.13767 0.13045 -0.0419 0.0501 1.0000
18.000 1.0559 0.14789 0.14096 -0.0480 0.0504 1.0000
18.250 1.0133 0.16351 0.15684 -0.0579 0.0513 1.0000
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