NACA 63(3)-218 (naca633218-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(3)-218 (naca633218-il) Reynolds number: 50,000 Max Cl/Cd: 22.19 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca633218-il-50000.txt Download as CSV file: xf-naca633218-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(3)-218
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7869 0.07099 0.06357 -0.0571 1.0000 0.1540
-12.000 -0.8156 0.06611 0.05855 -0.0572 1.0000 0.1536
-11.750 -0.8438 0.06216 0.05443 -0.0560 1.0000 0.1535
-11.500 -0.8682 0.05890 0.05097 -0.0536 1.0000 0.1537
-11.250 -0.8865 0.05583 0.04763 -0.0511 1.0000 0.1542
-11.000 -0.8560 0.05280 0.04478 -0.0517 1.0000 0.1598
-10.750 -0.8566 0.05041 0.04227 -0.0498 1.0000 0.1636
-10.500 -0.8653 0.04816 0.03981 -0.0468 1.0000 0.1666
-10.250 -0.8786 0.04634 0.03774 -0.0428 1.0000 0.1691
-10.000 -0.8697 0.04434 0.03576 -0.0406 1.0000 0.1740
-9.750 -0.8652 0.04292 0.03434 -0.0377 1.0000 0.1798
-9.500 -0.8733 0.04164 0.03287 -0.0335 1.0000 0.1846
-9.250 -0.8616 0.04020 0.03158 -0.0314 1.0000 0.1936
-9.000 -0.8635 0.03894 0.03016 -0.0278 1.0000 0.2018
-8.750 -0.8503 0.03764 0.02908 -0.0257 1.0000 0.2151
-8.500 -0.8440 0.03646 0.02804 -0.0229 1.0000 0.2306
-8.250 -0.8417 0.03527 0.02701 -0.0197 1.0000 0.2502
-8.000 -0.8407 0.03407 0.02610 -0.0163 1.0000 0.2757
-7.750 -0.8418 0.03302 0.02548 -0.0125 1.0000 0.3103
-7.500 -0.8422 0.03259 0.02557 -0.0082 1.0000 0.3567
-7.250 -0.8370 0.03350 0.02687 -0.0036 1.0000 0.4095
-7.000 -0.8175 0.03652 0.03010 0.0014 1.0000 0.4526
-6.750 -0.7993 0.03933 0.03291 0.0062 1.0000 0.4852
-6.500 -0.7524 0.04546 0.03902 0.0115 1.0000 0.5095
-6.250 -0.7240 0.04840 0.04181 0.0149 0.9980 0.5354
-6.000 -0.5753 0.05853 0.05150 0.0124 0.9912 0.5661
-5.750 -0.5517 0.05811 0.05090 0.0112 0.9819 0.5928
-5.500 -0.4202 0.06103 0.05340 0.0026 0.9773 0.6229
-5.250 -0.3779 0.06058 0.05276 -0.0006 0.9694 0.6463
-5.000 -0.3431 0.06004 0.05207 -0.0028 0.9609 0.6672
-4.750 -0.2751 0.05936 0.05118 -0.0091 0.9539 0.6912
-4.500 -0.2588 0.05864 0.05036 -0.0096 0.9435 0.7074
-4.250 -0.1615 0.05729 0.04878 -0.0201 0.9377 0.7324
-4.000 -0.1488 0.05654 0.04796 -0.0202 0.9258 0.7446
-3.750 -0.0853 0.05515 0.04641 -0.0273 0.9188 0.7627
-3.500 -0.0340 0.05381 0.04497 -0.0324 0.9086 0.7777
-3.250 0.0253 0.05223 0.04327 -0.0391 0.8999 0.7937
-3.000 0.0461 0.05139 0.04236 -0.0402 0.8879 0.8009
-2.750 0.0925 0.05007 0.04097 -0.0443 0.8759 0.8134
-2.500 0.1178 0.04922 0.04004 -0.0459 0.8667 0.8197
-2.250 0.1485 0.04829 0.03909 -0.0474 0.8537 0.8282
-2.000 0.1641 0.04780 0.03857 -0.0470 0.8414 0.8332
-1.750 0.1800 0.04724 0.03796 -0.0464 0.8310 0.8384
-1.500 0.2078 0.04648 0.03720 -0.0474 0.8166 0.8455
-1.250 0.2228 0.04606 0.03676 -0.0464 0.8030 0.8502
-1.000 0.2412 0.04541 0.03605 -0.0456 0.7926 0.8557
-0.750 0.2576 0.04497 0.03562 -0.0447 0.7766 0.8608
-0.500 0.2753 0.04460 0.03524 -0.0440 0.7609 0.8660
-0.250 0.2848 0.04436 0.03499 -0.0419 0.7461 0.8709
0.000 0.3076 0.04359 0.03417 -0.0413 0.7355 0.8767
0.250 0.3265 0.04338 0.03397 -0.0410 0.7191 0.8818
0.500 0.3335 0.04352 0.03410 -0.0388 0.7036 0.8868
0.750 0.3337 0.04365 0.03420 -0.0354 0.6924 0.8923
1.000 0.3685 0.04326 0.03381 -0.0376 0.6813 0.8984
1.250 0.3683 0.04407 0.03464 -0.0352 0.6689 0.9039
1.500 0.3799 0.04408 0.03462 -0.0336 0.6620 0.9103
1.750 0.3896 0.04518 0.03576 -0.0335 0.6521 0.9168
2.000 0.3898 0.04596 0.03654 -0.0312 0.6451 0.9235
2.250 0.4341 0.04529 0.03588 -0.0343 0.6413 0.9304
2.500 0.3755 0.04930 0.03994 -0.0272 0.6319 0.9381
2.750 0.3877 0.05043 0.04110 -0.0279 0.6274 0.9461
3.000 0.4125 0.05080 0.04149 -0.0290 0.6242 0.9545
3.250 0.4685 0.05054 0.04128 -0.0345 0.6220 0.9621
3.500 0.4006 0.05532 0.04609 -0.0286 0.6191 0.9726
3.750 0.3975 0.05762 0.04842 -0.0292 0.6185 0.9825
4.000 0.4150 0.05962 0.05047 -0.0325 0.6192 0.9921
4.250 0.4353 0.06142 0.05234 -0.0358 0.6204 1.0000
4.500 0.3533 0.06439 0.05524 -0.0272 0.6300 1.0000
4.750 0.3317 0.06558 0.05640 -0.0236 0.6364 1.0000
5.000 0.3289 0.06640 0.05722 -0.0215 0.6409 1.0000
5.250 0.1311 0.06956 0.06027 -0.0071 0.7921 1.0000
5.500 0.1279 0.06911 0.05979 -0.0053 0.7904 1.0000
5.750 0.1342 0.06909 0.05974 -0.0049 0.7842 1.0000
6.000 0.1594 0.07060 0.06124 -0.0070 0.7777 1.0000
6.250 0.1943 0.07340 0.06404 -0.0106 0.7738 1.0000
6.500 0.2031 0.07404 0.06467 -0.0107 0.7703 1.0000
6.750 0.2172 0.07480 0.06545 -0.0112 0.7621 1.0000
7.000 0.2500 0.07743 0.06812 -0.0142 0.7560 1.0000
7.250 0.2661 0.07913 0.06984 -0.0151 0.7514 1.0000
7.500 0.2865 0.08046 0.07122 -0.0161 0.7384 1.0000
7.750 0.3009 0.08196 0.07277 -0.0166 0.7273 1.0000
8.000 0.3398 0.08568 0.07658 -0.0199 0.7148 1.0000
8.250 0.3673 0.08827 0.07928 -0.0215 0.6964 1.0000
8.500 0.3738 0.08938 0.08046 -0.0211 0.6755 1.0000
8.750 0.3958 0.09138 0.08258 -0.0218 0.6439 1.0000
9.000 0.4349 0.09376 0.08506 -0.0227 0.6019 1.0000
9.250 0.5216 0.08730 0.07872 -0.0182 0.5027 1.0000
9.500 0.5729 0.08645 0.07802 -0.0175 0.4752 1.0000
9.750 0.5790 0.08822 0.07987 -0.0170 0.4517 1.0000
10.000 0.6140 0.08782 0.07960 -0.0160 0.4287 1.0000
10.250 0.6735 0.08439 0.07639 -0.0137 0.4067 1.0000
10.500 0.6641 0.08780 0.07983 -0.0136 0.3850 1.0000
10.750 0.7351 0.08088 0.07317 -0.0095 0.3607 1.0000
11.000 1.0009 0.04511 0.03739 0.0048 0.2907 1.0000
11.250 0.9711 0.04950 0.04194 0.0061 0.2729 1.0000
11.500 0.9327 0.05596 0.04858 0.0058 0.2599 1.0000
11.750 0.9822 0.05050 0.04224 0.0088 0.2270 1.0000
12.250 1.1252 0.05417 0.04491 0.0084 0.1681 1.0000
12.500 1.1576 0.05738 0.04815 0.0076 0.1583 1.0000
12.750 1.1404 0.06037 0.05151 0.0097 0.1562 1.0000
13.000 1.1247 0.06380 0.05525 0.0111 0.1539 1.0000
13.250 1.1128 0.06749 0.05918 0.0119 0.1512 1.0000
13.500 1.1356 0.07064 0.06232 0.0117 0.1452 1.0000
13.750 1.1074 0.07529 0.06727 0.0122 0.1449 1.0000
14.000 1.0774 0.08075 0.07298 0.0117 0.1449 1.0000
14.250 1.0430 0.08729 0.07976 0.0101 0.1453 1.0000
14.500 1.0066 0.09506 0.08772 0.0074 0.1460 1.0000
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