NACA 65(3)-618 (naca653618-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(3)-618 (naca653618-il) Reynolds number: 100,000 Max Cl/Cd: 28.98 at α=10.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca653618-il-100000-n5.txt Download as CSV file: xf-naca653618-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4159 0.08639 0.08113 -0.0932 0.9771 0.0415
-12.500 -0.4664 0.07274 0.06720 -0.1047 0.9696 0.0407
-12.250 -0.4947 0.06489 0.05904 -0.1112 0.9610 0.0405
-12.000 -0.5110 0.05931 0.05316 -0.1156 0.9522 0.0405
-11.750 -0.5185 0.05491 0.04845 -0.1189 0.9443 0.0409
-11.500 -0.5258 0.05154 0.04478 -0.1201 0.9335 0.0414
-11.250 -0.5277 0.04831 0.04117 -0.1212 0.9251 0.0421
-11.000 -0.5348 0.04603 0.03857 -0.1196 0.9130 0.0427
-10.750 -0.5351 0.04372 0.03587 -0.1183 0.9040 0.0433
-10.500 -0.5302 0.04159 0.03332 -0.1170 0.8955 0.0438
-10.250 -0.5151 0.03947 0.03086 -0.1169 0.8899 0.0443
-10.000 -0.5001 0.03808 0.02942 -0.1159 0.8818 0.0451
-9.750 -0.4787 0.03670 0.02791 -0.1160 0.8764 0.0463
-9.500 -0.4592 0.03542 0.02647 -0.1156 0.8707 0.0475
-9.250 -0.4420 0.03418 0.02504 -0.1146 0.8637 0.0485
-9.000 -0.4168 0.03277 0.02339 -0.1147 0.8591 0.0495
-8.750 -0.3897 0.03148 0.02188 -0.1149 0.8550 0.0506
-8.500 -0.3698 0.03055 0.02085 -0.1139 0.8479 0.0516
-8.250 -0.3447 0.02960 0.01993 -0.1139 0.8430 0.0532
-8.000 -0.3176 0.02871 0.01898 -0.1141 0.8393 0.0551
-7.750 -0.2984 0.02808 0.01829 -0.1130 0.8333 0.0568
-7.500 -0.2771 0.02742 0.01754 -0.1120 0.8278 0.0583
-7.250 -0.2540 0.02665 0.01675 -0.1115 0.8235 0.0599
-7.000 -0.2348 0.02599 0.01609 -0.1106 0.8190 0.0619
-6.750 -0.2229 0.02560 0.01570 -0.1084 0.8120 0.0645
-6.500 -0.2045 0.02510 0.01510 -0.1073 0.8073 0.0679
-6.250 -0.1852 0.02443 0.01442 -0.1064 0.8038 0.0714
-6.000 -0.1739 0.02412 0.01409 -0.1042 0.7977 0.0752
-5.750 -0.1591 0.02368 0.01362 -0.1025 0.7923 0.0806
-5.500 -0.1398 0.02310 0.01302 -0.1016 0.7884 0.0908
-5.250 -0.1200 0.02231 0.01235 -0.1010 0.7852 0.1128
-5.000 -0.1143 0.02179 0.01212 -0.0982 0.7781 0.1577
-4.750 -0.1057 0.02039 0.01144 -0.0968 0.7734 0.2943
-4.500 -0.0904 0.01974 0.01181 -0.0947 0.7703 0.4900
-4.250 -0.0617 0.01991 0.01195 -0.0945 0.7680 0.5509
-4.000 -0.0468 0.02031 0.01229 -0.0925 0.7616 0.5789
-3.750 -0.0253 0.02112 0.01314 -0.0903 0.7574 0.6178
-3.500 -0.0020 0.02220 0.01421 -0.0876 0.7543 0.6509
-3.250 0.0248 0.02276 0.01469 -0.0862 0.7519 0.6681
-3.000 0.0451 0.02312 0.01501 -0.0844 0.7480 0.6733
-2.750 0.0620 0.02331 0.01512 -0.0828 0.7429 0.6796
-2.500 0.0877 0.02315 0.01482 -0.0832 0.7394 0.6864
-2.250 0.1151 0.02316 0.01474 -0.0830 0.7367 0.6895
-2.000 0.1452 0.02306 0.01452 -0.0835 0.7345 0.6932
-1.750 0.1640 0.02318 0.01459 -0.0825 0.7301 0.6979
-1.500 0.1835 0.02323 0.01455 -0.0822 0.7253 0.7037
-1.250 0.2073 0.02332 0.01459 -0.0817 0.7221 0.7064
-1.000 0.2349 0.02331 0.01452 -0.0818 0.7197 0.7095
-0.750 0.2657 0.02321 0.01434 -0.0825 0.7177 0.7128
-0.500 0.2892 0.02330 0.01438 -0.0824 0.7142 0.7170
-0.250 0.3025 0.02368 0.01473 -0.0811 0.7084 0.7225
0.000 0.3246 0.02385 0.01490 -0.0803 0.7052 0.7250
0.250 0.3521 0.02388 0.01490 -0.0805 0.7028 0.7278
0.500 0.3829 0.02383 0.01481 -0.0812 0.7009 0.7312
0.750 0.4162 0.02374 0.01467 -0.0825 0.6993 0.7352
1.000 0.4149 0.02469 0.01567 -0.0791 0.6913 0.7407
1.250 0.4355 0.02495 0.01595 -0.0782 0.6880 0.7434
1.500 0.4630 0.02502 0.01602 -0.0783 0.6857 0.7464
1.750 0.4943 0.02499 0.01599 -0.0791 0.6839 0.7500
2.000 0.5287 0.02491 0.01589 -0.0806 0.6824 0.7543
2.500 0.5359 0.02665 0.01777 -0.0744 0.6698 0.7630
2.750 0.5663 0.02666 0.01780 -0.0750 0.6678 0.7665
3.000 0.5995 0.02663 0.01779 -0.0762 0.6663 0.7707
3.250 0.6352 0.02657 0.01775 -0.0779 0.6650 0.7755
3.750 0.6294 0.02877 0.02012 -0.0697 0.6508 0.7852
4.000 0.6637 0.02863 0.02003 -0.0709 0.6493 0.7898
5.000 0.6882 0.03334 0.02504 -0.0624 0.6213 0.8130
5.250 0.7143 0.03328 0.02507 -0.0620 0.6185 0.8179
5.500 0.7468 0.03295 0.02482 -0.0625 0.6167 0.8236
5.750 0.7843 0.03247 0.02441 -0.0638 0.6154 0.8296
6.250 0.7969 0.03470 0.02686 -0.0595 0.6000 0.8436
6.500 0.8320 0.03400 0.02627 -0.0599 0.5986 0.8500
7.250 0.8418 0.03792 0.03053 -0.0531 0.5701 0.8778
7.500 0.8735 0.03696 0.02970 -0.0527 0.5675 0.8869
7.750 0.9124 0.03556 0.02844 -0.0529 0.5656 0.8973
8.250 0.9207 0.03751 0.03066 -0.0483 0.5447 0.9319
8.750 0.9898 0.03526 0.02871 -0.0491 0.5320 1.0000
9.250 0.9992 0.03805 0.03165 -0.0468 0.4953 1.0000
9.500 1.0166 0.03810 0.03173 -0.0460 0.4701 1.0000
9.750 1.0362 0.03798 0.03154 -0.0451 0.4359 1.0000
10.000 1.0647 0.03713 0.03046 -0.0445 0.3910 1.0000
10.250 1.0821 0.03734 0.03031 -0.0433 0.3406 1.0000
10.500 1.0840 0.03917 0.03184 -0.0416 0.2954 1.0000
10.750 1.0807 0.04162 0.03401 -0.0401 0.2528 1.0000
11.000 1.0765 0.04433 0.03646 -0.0387 0.2131 1.0000
11.250 1.0730 0.04712 0.03900 -0.0375 0.1749 1.0000
11.500 1.0706 0.04991 0.04154 -0.0366 0.1384 1.0000
11.750 1.0691 0.05272 0.04412 -0.0358 0.1071 1.0000
12.000 1.0702 0.05537 0.04660 -0.0352 0.0853 1.0000
12.250 1.0728 0.05794 0.04906 -0.0347 0.0722 1.0000
12.500 1.0769 0.06042 0.05152 -0.0343 0.0638 1.0000
12.750 1.0822 0.06284 0.05398 -0.0340 0.0578 1.0000
13.000 1.0862 0.06542 0.05656 -0.0338 0.0537 1.0000
13.250 1.0921 0.06784 0.05907 -0.0337 0.0501 1.0000
13.500 1.0960 0.07051 0.06175 -0.0337 0.0475 1.0000
13.750 1.1027 0.07289 0.06422 -0.0336 0.0449 1.0000
14.000 1.1092 0.07532 0.06672 -0.0336 0.0430 1.0000
14.250 1.1149 0.07782 0.06925 -0.0337 0.0414 1.0000
14.500 1.1224 0.08011 0.07162 -0.0337 0.0398 1.0000
14.750 1.1314 0.08226 0.07388 -0.0337 0.0381 1.0000
15.000 1.1397 0.08451 0.07618 -0.0338 0.0366 1.0000
15.250 1.1486 0.08666 0.07834 -0.0340 0.0355 1.0000
15.500 1.1597 0.08851 0.08022 -0.0339 0.0345 1.0000
15.750 1.1716 0.09035 0.08222 -0.0338 0.0336 1.0000
16.000 1.1832 0.09228 0.08427 -0.0338 0.0327 1.0000
16.250 1.1933 0.09442 0.08652 -0.0340 0.0318 1.0000
16.500 1.2026 0.09665 0.08884 -0.0343 0.0310 1.0000
16.750 1.2128 0.09874 0.09095 -0.0347 0.0303 1.0000
17.000 1.2216 0.10110 0.09341 -0.0350 0.0296 1.0000
17.250 1.2240 0.10447 0.09704 -0.0358 0.0289 1.0000
17.500 1.2260 0.10793 0.10073 -0.0368 0.0284 1.0000
17.750 1.2268 0.11160 0.10462 -0.0379 0.0280 1.0000
18.000 1.2262 0.11552 0.10875 -0.0393 0.0276 1.0000
18.250 1.2234 0.11981 0.11326 -0.0409 0.0274 1.0000
18.500 1.2185 0.12452 0.11818 -0.0430 0.0271 1.0000
18.750 1.2113 0.12970 0.12358 -0.0455 0.0269 1.0000
19.000 1.2014 0.13549 0.12960 -0.0486 0.0268 1.0000
19.250 1.1879 0.14215 0.13650 -0.0524 0.0267 1.0000
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