NACA 65(3)-618 (naca653618-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(3)-618 (naca653618-il) Reynolds number: 100,000 Max Cl/Cd: 27.83 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca653618-il-100000.txt Download as CSV file: xf-naca653618-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3556 0.11886 0.11426 -0.0627 0.9828 0.1634
-11.000 -0.3290 0.11590 0.11124 -0.0636 0.9779 0.1692
-10.750 -0.3472 0.11010 0.10550 -0.0708 0.9725 0.1790
-10.500 -0.3053 0.10734 0.10265 -0.0716 0.9703 0.1859
-10.250 -0.3205 0.10270 0.09807 -0.0757 0.9628 0.1965
-10.000 -0.2928 0.09992 0.09524 -0.0773 0.9590 0.2058
-9.750 -0.2821 0.09541 0.09071 -0.0813 0.9559 0.2160
-9.500 -0.3064 0.09162 0.08701 -0.0838 0.9464 0.2295
-9.250 -0.2727 0.08838 0.08370 -0.0852 0.9433 0.2337
-9.000 -0.5878 0.05911 0.05298 -0.0906 0.9098 0.0979
-8.750 -0.5752 0.05409 0.04761 -0.0915 0.9062 0.0924
-8.500 -0.6054 0.05218 0.04484 -0.0844 0.8960 0.0874
-8.250 -0.5859 0.04999 0.04224 -0.0844 0.8914 0.0870
-8.000 -0.5562 0.04722 0.03906 -0.0860 0.8885 0.0868
-7.750 -0.5590 0.04582 0.03752 -0.0818 0.8812 0.0865
-7.500 -0.5420 0.04383 0.03526 -0.0809 0.8767 0.0863
-7.250 -0.5144 0.04196 0.03305 -0.0815 0.8734 0.0866
-7.000 -0.4788 0.03953 0.03049 -0.0836 0.8712 0.0889
-6.750 -0.4782 0.03904 0.02995 -0.0796 0.8644 0.0899
-6.500 -0.4586 0.03813 0.02894 -0.0787 0.8597 0.0916
-6.250 -0.4290 0.03708 0.02779 -0.0791 0.8566 0.0936
-6.000 -0.3941 0.03614 0.02673 -0.0803 0.8543 0.0966
-5.750 -0.3812 0.03597 0.02643 -0.0782 0.8500 0.0991
-5.500 -0.3750 0.03559 0.02611 -0.0751 0.8445 0.1018
-5.250 -0.3517 0.03496 0.02560 -0.0746 0.8408 0.1061
-5.000 -0.3226 0.03441 0.02505 -0.0749 0.8380 0.1120
-4.750 -0.2910 0.03368 0.02446 -0.0759 0.8359 0.1216
-4.500 -0.3012 0.03412 0.02490 -0.0707 0.8305 0.1263
-4.250 -0.2892 0.03381 0.02469 -0.0691 0.8262 0.1392
-4.000 -0.2660 0.03232 0.02379 -0.0699 0.8229 0.2108
-3.750 -0.2511 0.03211 0.02554 -0.0667 0.8203 0.6193
-3.500 -0.2262 0.03372 0.02709 -0.0638 0.8181 0.6557
-3.250 -0.2381 0.03475 0.02809 -0.0583 0.8135 0.6696
-3.000 -0.2306 0.03580 0.02909 -0.0544 0.8094 0.6867
-2.750 -0.2198 0.03694 0.03019 -0.0504 0.8065 0.7032
-2.500 -0.2097 0.03823 0.03147 -0.0458 0.8043 0.7231
-2.250 -0.2071 0.04000 0.03333 -0.0373 0.8021 0.7466
-2.000 -0.2144 0.04129 0.03465 -0.0294 0.7990 0.7674
-1.750 -0.2244 0.04219 0.03557 -0.0224 0.7968 0.7849
-1.500 -0.2275 0.04296 0.03633 -0.0167 0.7960 0.8019
-1.250 -0.2209 0.04331 0.03661 -0.0140 0.7941 0.8134
-1.000 -0.2094 0.04360 0.03682 -0.0124 0.7923 0.8201
-0.750 -0.1924 0.04397 0.03708 -0.0132 0.7924 0.8269
-0.500 -0.1837 0.04434 0.03741 -0.0112 0.7928 0.8317
-0.250 -0.1882 0.04524 0.03831 -0.0091 0.8068 0.8373
0.000 -0.1511 0.04579 0.03872 -0.0121 0.8030 0.8424
0.250 -0.1234 0.04648 0.03932 -0.0133 0.8016 0.8466
0.500 -0.1846 0.04742 0.04043 -0.0048 0.8482 0.8526
0.750 -0.1585 0.04777 0.04069 -0.0062 0.8409 0.8576
1.000 -0.1193 0.04909 0.04190 -0.0095 0.8367 0.8619
1.250 -0.1011 0.04988 0.04264 -0.0093 0.8345 0.8661
1.500 -0.0929 0.04933 0.04207 -0.0077 0.8246 0.8714
1.750 -0.0532 0.05065 0.04329 -0.0112 0.8199 0.8764
2.000 -0.0308 0.05179 0.04441 -0.0116 0.8174 0.8807
2.250 -0.0249 0.05122 0.04383 -0.0097 0.8068 0.8860
2.500 0.0151 0.05270 0.04525 -0.0130 0.8023 0.8917
2.750 0.0184 0.05286 0.04542 -0.0107 0.7968 0.8973
3.000 0.0433 0.05338 0.04592 -0.0115 0.7881 0.9031
3.250 0.0895 0.05545 0.04794 -0.0155 0.7841 0.9089
3.500 0.0808 0.05476 0.04728 -0.0117 0.7743 0.9161
3.750 0.1218 0.05615 0.04866 -0.0146 0.7681 0.9237
4.000 0.1236 0.05639 0.04892 -0.0127 0.7602 0.9318
4.250 0.1617 0.05743 0.04997 -0.0151 0.7519 0.9398
4.500 0.1716 0.05813 0.05070 -0.0147 0.7441 0.9496
4.750 0.2390 0.05981 0.05239 -0.0204 0.7329 0.9592
5.000 0.2375 0.05988 0.05254 -0.0195 0.7213 0.9702
5.250 0.3300 0.05703 0.04963 -0.0243 0.6717 0.9799
5.500 0.3695 0.05745 0.05009 -0.0271 0.6618 1.0000
5.750 0.3989 0.05818 0.05085 -0.0292 0.6532 1.0000
6.000 0.4257 0.05902 0.05172 -0.0310 0.6429 1.0000
6.250 0.4672 0.05946 0.05220 -0.0339 0.6356 1.0000
6.500 0.4870 0.06060 0.05340 -0.0352 0.6246 1.0000
6.750 0.5341 0.06075 0.05360 -0.0382 0.6185 1.0000
7.000 0.5504 0.06202 0.05493 -0.0391 0.6064 1.0000
7.250 0.6023 0.06172 0.05470 -0.0422 0.6014 1.0000
7.500 0.6154 0.06312 0.05616 -0.0427 0.5886 1.0000
7.750 0.6700 0.06234 0.05549 -0.0454 0.5845 1.0000
8.000 0.6813 0.06375 0.05696 -0.0456 0.5711 1.0000
8.250 0.7382 0.06240 0.05574 -0.0480 0.5678 1.0000
8.500 0.7499 0.06361 0.05702 -0.0478 0.5539 1.0000
8.750 0.8078 0.06166 0.05520 -0.0497 0.5511 1.0000
9.000 0.8201 0.06263 0.05627 -0.0493 0.5371 1.0000
10.000 1.0522 0.04469 0.03900 -0.0496 0.5046 1.0000
10.250 1.0823 0.04281 0.03727 -0.0486 0.4892 1.0000
10.500 1.0952 0.04284 0.03740 -0.0471 0.4680 1.0000
10.750 1.1210 0.04156 0.03619 -0.0459 0.4395 1.0000
11.000 1.1398 0.04095 0.03542 -0.0441 0.3879 1.0000
11.250 1.1412 0.04186 0.03558 -0.0410 0.2980 1.0000
11.500 1.1194 0.04579 0.03890 -0.0383 0.2258 1.0000
11.750 1.0964 0.05029 0.04280 -0.0361 0.1664 1.0000
12.000 1.0815 0.05431 0.04631 -0.0344 0.1290 1.0000
12.250 1.0804 0.05711 0.04890 -0.0331 0.1082 1.0000
12.500 1.0864 0.05923 0.05087 -0.0321 0.0961 1.0000
12.750 1.0975 0.06086 0.05235 -0.0312 0.0872 1.0000
13.000 1.1132 0.06213 0.05356 -0.0305 0.0804 1.0000
13.250 1.1391 0.06263 0.05399 -0.0296 0.0750 1.0000
13.500 1.1620 0.06356 0.05490 -0.0291 0.0704 1.0000
13.750 1.1969 0.06400 0.05524 -0.0287 0.0661 1.0000
14.000 1.2248 0.06518 0.05658 -0.0284 0.0634 1.0000
14.250 1.2544 0.06653 0.05804 -0.0283 0.0612 1.0000
14.500 1.3111 0.06786 0.05922 -0.0295 0.0581 1.0000
14.750 1.3133 0.07068 0.06238 -0.0287 0.0574 1.0000
15.000 1.3150 0.07378 0.06581 -0.0280 0.0565 1.0000
15.250 1.3164 0.07716 0.06952 -0.0274 0.0559 1.0000
15.500 1.3152 0.08091 0.07358 -0.0270 0.0557 1.0000
15.750 1.3095 0.08503 0.07802 -0.0266 0.0556 1.0000
16.000 1.2993 0.08955 0.08285 -0.0265 0.0556 1.0000
16.250 1.2855 0.09446 0.08805 -0.0267 0.0558 1.0000
16.500 1.2687 0.09977 0.09365 -0.0274 0.0561 1.0000
16.750 1.2501 0.10547 0.09962 -0.0285 0.0564 1.0000
17.000 1.2299 0.11159 0.10599 -0.0302 0.0568 1.0000
17.250 1.2096 0.11806 0.11268 -0.0325 0.0572 1.0000
17.500 1.1904 0.12482 0.11963 -0.0352 0.0576 1.0000
17.750 1.1773 0.13142 0.12637 -0.0379 0.0581 1.0000
18.000 0.9885 0.17842 0.17399 -0.0685 0.0686 1.0000
18.250 1.0081 0.17772 0.17330 -0.0672 0.0679 1.0000
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