NACA 65(3)-618 (naca653618-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(3)-618 (naca653618-il) Reynolds number: 200,000 Max Cl/Cd: 67.65 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca653618-il-200000.txt Download as CSV file: xf-naca653618-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2931 0.11126 0.10770 -0.0820 0.9815 0.0790
-12.250 -0.2831 0.10678 0.10321 -0.0861 0.9767 0.0824
-12.000 -0.3301 0.09065 0.08715 -0.1028 0.9720 0.0880
-11.750 -0.2875 0.09197 0.08842 -0.1001 0.9704 0.0896
-11.500 -0.1500 0.07578 0.07226 -0.1160 0.9459 0.1031
-11.250 -0.1312 0.07293 0.06938 -0.1177 0.9416 0.1070
-10.500 -0.4950 0.04298 0.03718 -0.1271 0.9132 0.0547
-10.250 -0.4830 0.03963 0.03358 -0.1269 0.9071 0.0541
-10.000 -0.4788 0.03772 0.03137 -0.1245 0.8980 0.0543
-9.750 -0.4677 0.03566 0.02897 -0.1232 0.8912 0.0546
-9.500 -0.4513 0.03352 0.02654 -0.1223 0.8857 0.0545
-9.250 -0.4371 0.03180 0.02459 -0.1207 0.8778 0.0545
-9.000 -0.4160 0.03021 0.02270 -0.1201 0.8727 0.0549
-8.750 -0.3973 0.02899 0.02122 -0.1190 0.8668 0.0556
-8.500 -0.3724 0.02707 0.01928 -0.1189 0.8610 0.0569
-8.250 -0.3454 0.02584 0.01797 -0.1190 0.8566 0.0579
-8.000 -0.3163 0.02474 0.01677 -0.1193 0.8532 0.0589
-7.750 -0.2953 0.02402 0.01602 -0.1183 0.8467 0.0601
-7.500 -0.2708 0.02329 0.01521 -0.1178 0.8415 0.0618
-7.250 -0.2441 0.02260 0.01440 -0.1177 0.8375 0.0636
-7.000 -0.2198 0.02184 0.01361 -0.1171 0.8328 0.0652
-6.750 -0.2006 0.02110 0.01295 -0.1159 0.8269 0.0671
-6.500 -0.1797 0.02051 0.01237 -0.1150 0.8225 0.0694
-6.250 -0.1568 0.01996 0.01176 -0.1144 0.8190 0.0727
-6.000 -0.1418 0.01961 0.01141 -0.1127 0.8133 0.0758
-5.750 -0.1268 0.01903 0.01087 -0.1111 0.8079 0.0800
-5.500 -0.1055 0.01852 0.01030 -0.1104 0.8040 0.0860
-5.250 -0.0841 0.01781 0.00960 -0.1099 0.8009 0.0978
-5.000 -0.0744 0.01713 0.00923 -0.1079 0.7945 0.1369
-4.750 -0.0716 0.01476 0.00867 -0.1062 0.7896 0.4987
-4.500 -0.0437 0.01503 0.00899 -0.1058 0.7866 0.5729
-4.250 -0.0135 0.01533 0.00920 -0.1059 0.7842 0.6012
-4.000 0.0079 0.01580 0.00967 -0.1046 0.7790 0.6185
-3.750 0.0334 0.01614 0.00993 -0.1040 0.7746 0.6337
-3.500 0.0602 0.01656 0.01036 -0.1031 0.7714 0.6467
-3.250 0.0868 0.01733 0.01111 -0.1016 0.7688 0.6679
-3.000 0.1122 0.01834 0.01214 -0.0994 0.7666 0.6865
-2.750 0.1261 0.01923 0.01317 -0.0955 0.7615 0.6936
-2.500 0.1504 0.01940 0.01328 -0.0950 0.7575 0.7021
-2.250 0.1779 0.01934 0.01313 -0.0951 0.7545 0.7069
-2.000 0.2065 0.01936 0.01309 -0.0950 0.7520 0.7101
-1.750 0.2366 0.01936 0.01301 -0.0955 0.7500 0.7140
-1.500 0.2551 0.01950 0.01315 -0.0948 0.7452 0.7193
-1.250 0.2799 0.01948 0.01308 -0.0951 0.7414 0.7237
-1.000 0.3059 0.01949 0.01307 -0.0949 0.7384 0.7262
-0.750 0.3351 0.01945 0.01297 -0.0952 0.7360 0.7291
-0.500 0.3663 0.01938 0.01284 -0.0961 0.7340 0.7325
-0.250 0.3898 0.01953 0.01298 -0.0962 0.7305 0.7367
0.000 0.4109 0.01974 0.01318 -0.0960 0.7261 0.7411
0.250 0.4343 0.01986 0.01332 -0.0954 0.7228 0.7436
0.500 0.4626 0.01985 0.01330 -0.0957 0.7203 0.7463
0.750 0.4939 0.01980 0.01321 -0.0966 0.7183 0.7494
1.000 0.5267 0.01978 0.01315 -0.0979 0.7166 0.7532
1.250 0.5410 0.02036 0.01379 -0.0968 0.7115 0.7582
1.500 0.5597 0.02065 0.01413 -0.0956 0.7074 0.7607
1.750 0.5864 0.02072 0.01422 -0.0956 0.7046 0.7636
2.000 0.6161 0.02076 0.01426 -0.0962 0.7025 0.7669
2.250 0.6490 0.02075 0.01424 -0.0975 0.7008 0.7709
2.500 0.6860 0.02072 0.01417 -0.0997 0.6993 0.7755
2.750 0.6761 0.02198 0.01562 -0.0941 0.6911 0.7789
3.000 0.7026 0.02210 0.01577 -0.0942 0.6883 0.7822
3.250 0.7343 0.02206 0.01576 -0.0951 0.6861 0.7860
3.500 0.7701 0.02195 0.01566 -0.0968 0.6844 0.7904
3.750 0.8069 0.02183 0.01554 -0.0986 0.6828 0.7944
4.000 0.7886 0.02340 0.01729 -0.0918 0.6732 0.7991
4.250 0.8224 0.02321 0.01715 -0.0928 0.6707 0.8033
4.500 0.8608 0.02295 0.01691 -0.0948 0.6687 0.8079
4.750 0.9002 0.02262 0.01660 -0.0969 0.6670 0.8118
5.000 0.8822 0.02418 0.01834 -0.0901 0.6576 0.8171
5.250 0.9175 0.02389 0.01810 -0.0913 0.6548 0.8222
5.500 0.9603 0.02339 0.01764 -0.0939 0.6525 0.8276
5.750 1.0033 0.02267 0.01697 -0.0959 0.6504 0.8313
6.000 0.9952 0.02372 0.01818 -0.0906 0.6414 0.8380
6.250 1.0413 0.02285 0.01734 -0.0933 0.6375 0.8435
6.500 1.0970 0.02139 0.01589 -0.0970 0.6338 0.8471
6.750 1.1016 0.02152 0.01615 -0.0930 0.6239 0.8542
7.000 1.1488 0.01977 0.01435 -0.0951 0.6116 0.8605
7.250 1.1809 0.01860 0.01315 -0.0947 0.5991 0.8659
7.500 1.1895 0.01847 0.01314 -0.0912 0.5874 0.8745
7.750 1.1990 0.01830 0.01307 -0.0877 0.5768 0.8824
8.000 1.2167 0.01799 0.01280 -0.0856 0.5654 0.8915
8.250 1.2150 0.01796 0.01288 -0.0802 0.5536 0.9029
8.500 1.2132 0.01811 0.01313 -0.0750 0.5402 0.9169
8.750 1.2137 0.01824 0.01334 -0.0704 0.5244 0.9339
9.000 1.2136 0.01839 0.01354 -0.0659 0.5052 0.9581
9.250 1.2221 0.01898 0.01409 -0.0643 0.4710 1.0000
9.500 1.2240 0.02028 0.01512 -0.0620 0.4173 1.0000
10.000 1.1982 0.02519 0.01930 -0.0552 0.3109 1.0000
10.250 1.1815 0.02824 0.02202 -0.0520 0.2610 1.0000
10.500 1.1641 0.03157 0.02502 -0.0491 0.2105 1.0000
10.750 1.1461 0.03518 0.02827 -0.0465 0.1582 1.0000
11.000 1.1299 0.03888 0.03157 -0.0443 0.1085 1.0000
11.250 1.1203 0.04220 0.03463 -0.0426 0.0810 1.0000
11.500 1.1178 0.04503 0.03736 -0.0414 0.0690 1.0000
11.750 1.1204 0.04746 0.03981 -0.0406 0.0620 1.0000
12.000 1.1211 0.05013 0.04244 -0.0398 0.0574 1.0000
12.250 1.1279 0.05225 0.04461 -0.0393 0.0534 1.0000
12.500 1.1304 0.05478 0.04711 -0.0387 0.0506 1.0000
12.750 1.1375 0.05690 0.04928 -0.0382 0.0482 1.0000
13.000 1.1462 0.05888 0.05130 -0.0378 0.0461 1.0000
13.250 1.1549 0.06084 0.05325 -0.0374 0.0443 1.0000
13.500 1.1659 0.06249 0.05484 -0.0367 0.0425 1.0000
13.750 1.1785 0.06412 0.05658 -0.0364 0.0409 1.0000
14.000 1.1921 0.06564 0.05814 -0.0361 0.0393 1.0000
14.250 1.2072 0.06697 0.05947 -0.0357 0.0380 1.0000
14.500 1.2367 0.06693 0.05927 -0.0349 0.0366 1.0000
14.750 1.2525 0.06842 0.06091 -0.0346 0.0360 1.0000
15.000 1.2691 0.06991 0.06254 -0.0342 0.0352 1.0000
15.250 1.2866 0.07141 0.06418 -0.0339 0.0345 1.0000
15.500 1.3025 0.07310 0.06601 -0.0337 0.0339 1.0000
15.750 1.3173 0.07491 0.06792 -0.0335 0.0331 1.0000
16.000 1.3309 0.07683 0.06992 -0.0335 0.0324 1.0000
16.250 1.3498 0.07848 0.07160 -0.0335 0.0317 1.0000
16.500 1.3772 0.08056 0.07378 -0.0334 0.0311 1.0000
16.750 1.3754 0.08402 0.07749 -0.0333 0.0310 1.0000
17.000 1.3715 0.08779 0.08151 -0.0334 0.0309 1.0000
17.250 1.3660 0.09183 0.08581 -0.0337 0.0309 1.0000
17.500 1.3591 0.09616 0.09038 -0.0342 0.0309 1.0000
17.750 1.3509 0.10072 0.09517 -0.0350 0.0309 1.0000
18.000 1.3410 0.10559 0.10027 -0.0361 0.0309 1.0000
18.250 1.3309 0.11067 0.10558 -0.0374 0.0310 1.0000
18.500 1.3228 0.11583 0.11092 -0.0389 0.0311 1.0000
18.750 1.3041 0.12147 0.11680 -0.0413 0.0313 1.0000
19.000 1.2697 0.12969 0.12539 -0.0456 0.0317 1.0000
19.250 1.1391 0.15912 0.15572 -0.0639 0.0342 1.0000
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Polar data table (+)
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