NACA 64(3)-218 (naca643218-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64(3)-218 (naca643218-il) Reynolds number: 100,000 Max Cl/Cd: 41.47 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca643218-il-100000.txt Download as CSV file: xf-naca643218-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64(3)-218
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.3403 0.14344 0.13857 -0.0230 1.0000 0.1541
-14.500 -0.3861 0.14360 0.13875 -0.0274 1.0000 0.1578
-14.250 -0.6465 0.10279 0.09731 -0.0494 1.0000 0.0873
-14.000 -0.6413 0.09810 0.09263 -0.0502 1.0000 0.0862
-13.750 -0.6732 0.08879 0.08324 -0.0550 1.0000 0.0842
-13.500 -0.7331 0.07804 0.07229 -0.0608 1.0000 0.0818
-13.250 -0.8088 0.06866 0.06251 -0.0643 1.0000 0.0791
-13.000 -0.8885 0.06416 0.05744 -0.0631 1.0000 0.0769
-12.750 -0.9046 0.06118 0.05424 -0.0615 1.0000 0.0767
-12.500 -0.9139 0.05803 0.05090 -0.0598 1.0000 0.0766
-12.250 -0.9231 0.05523 0.04791 -0.0575 1.0000 0.0766
-12.000 -0.9291 0.05260 0.04505 -0.0552 1.0000 0.0766
-11.750 -0.9327 0.05021 0.04241 -0.0528 1.0000 0.0767
-11.500 -0.9255 0.04710 0.03917 -0.0515 1.0000 0.0774
-11.250 -0.9123 0.04488 0.03696 -0.0506 1.0000 0.0792
-11.000 -0.9073 0.04355 0.03563 -0.0481 1.0000 0.0806
-10.750 -0.9163 0.04263 0.03464 -0.0434 1.0000 0.0813
-10.500 -0.9276 0.04191 0.03384 -0.0384 1.0000 0.0821
-10.250 -0.9349 0.04100 0.03281 -0.0340 1.0000 0.0831
-10.000 -0.9383 0.03997 0.03163 -0.0302 1.0000 0.0841
-9.750 -0.9291 0.03861 0.03006 -0.0284 0.9985 0.0856
-9.500 -0.8870 0.03636 0.02758 -0.0318 0.9931 0.0890
-9.250 -0.8442 0.03472 0.02603 -0.0352 0.9872 0.0943
-9.000 -0.8003 0.03325 0.02429 -0.0387 0.9816 0.0997
-8.750 -0.7543 0.03158 0.02289 -0.0421 0.9766 0.1080
-8.500 -0.7073 0.03008 0.02152 -0.0458 0.9720 0.1188
-8.250 -0.6700 0.02875 0.02034 -0.0483 0.9648 0.1330
-8.000 -0.6332 0.02726 0.01902 -0.0512 0.9584 0.1572
-7.750 -0.6173 0.02554 0.01770 -0.0516 0.9472 0.1909
-7.500 -0.6173 0.02344 0.01620 -0.0500 0.9343 0.2540
-7.250 -0.6216 0.02204 0.01602 -0.0465 0.9219 0.4039
-7.000 -0.5970 0.02261 0.01657 -0.0457 0.9127 0.4901
-6.750 -0.5738 0.02358 0.01743 -0.0441 0.9028 0.5226
-6.500 -0.5296 0.02528 0.01911 -0.0446 0.8970 0.5468
-6.250 -0.4803 0.02726 0.02104 -0.0452 0.8926 0.5662
-6.000 -0.4527 0.02861 0.02231 -0.0433 0.8828 0.5807
-5.750 -0.4125 0.02988 0.02346 -0.0433 0.8775 0.5960
-5.500 -0.3285 0.03357 0.02707 -0.0452 0.8761 0.6024
-5.250 -0.3173 0.03389 0.02733 -0.0424 0.8650 0.6155
-5.000 -0.2400 0.03647 0.02978 -0.0446 0.8625 0.6222
-4.750 -0.2272 0.03632 0.02954 -0.0426 0.8543 0.6344
-4.500 -0.1816 0.03715 0.03027 -0.0433 0.8478 0.6419
-4.250 -0.1689 0.03665 0.02967 -0.0414 0.8411 0.6527
-4.000 -0.1345 0.03705 0.03000 -0.0415 0.8331 0.6591
-3.750 -0.1419 0.03613 0.02901 -0.0380 0.8248 0.6699
-3.500 -0.0995 0.03640 0.02919 -0.0391 0.8199 0.6745
-3.250 -0.1324 0.03525 0.02802 -0.0335 0.8091 0.6865
-3.000 -0.0860 0.03545 0.02813 -0.0349 0.8056 0.6895
-2.750 -0.0622 0.03556 0.02821 -0.0344 0.7993 0.6941
-2.500 -0.0921 0.03439 0.02699 -0.0293 0.7902 0.7048
-2.250 -0.0531 0.03435 0.02688 -0.0301 0.7868 0.7074
-2.000 -0.0363 0.03461 0.02714 -0.0288 0.7796 0.7113
-1.750 -0.0297 0.03438 0.02688 -0.0269 0.7731 0.7171
-1.500 -0.0263 0.03345 0.02586 -0.0253 0.7688 0.7243
-1.250 -0.0088 0.03380 0.02622 -0.0240 0.7636 0.7275
-1.000 -0.0067 0.03421 0.02665 -0.0213 0.7564 0.7323
-0.750 0.0075 0.03377 0.02615 -0.0206 0.7521 0.7382
-0.500 0.0324 0.03323 0.02554 -0.0210 0.7493 0.7434
-0.250 0.0135 0.03443 0.02681 -0.0160 0.7406 0.7475
0.000 0.0251 0.03462 0.02699 -0.0147 0.7360 0.7521
0.250 0.0506 0.03430 0.02660 -0.0156 0.7329 0.7582
0.500 0.0832 0.03403 0.02631 -0.0167 0.7307 0.7622
0.750 0.0361 0.03587 0.02822 -0.0087 0.7210 0.7673
1.000 0.0553 0.03605 0.02839 -0.0085 0.7170 0.7723
1.250 0.0921 0.03590 0.02818 -0.0110 0.7143 0.7787
1.500 0.1311 0.03581 0.02811 -0.0121 0.7123 0.7822
1.750 0.0779 0.03778 0.03014 -0.0038 0.7033 0.7890
2.000 0.1015 0.03807 0.03041 -0.0045 0.6991 0.7953
2.250 0.1334 0.03817 0.03054 -0.0053 0.6961 0.7999
2.500 0.1772 0.03809 0.03049 -0.0071 0.6939 0.8046
2.750 0.1417 0.04006 0.03246 -0.0021 0.6853 0.8139
3.000 0.1607 0.04050 0.03295 -0.0013 0.6808 0.8198
3.250 0.1992 0.04047 0.03296 -0.0023 0.6773 0.8264
3.500 0.1937 0.04177 0.03430 -0.0001 0.6704 0.8348
3.750 0.2052 0.04243 0.03501 0.0014 0.6642 0.8423
4.000 0.2441 0.04243 0.03505 -0.0001 0.6599 0.8504
4.250 0.2413 0.04354 0.03623 0.0027 0.6522 0.8589
4.500 0.2601 0.04401 0.03675 0.0032 0.6452 0.8688
4.750 0.3001 0.04373 0.03656 0.0029 0.6412 0.8776
5.000 0.2881 0.04511 0.03799 0.0061 0.6301 0.8904
5.250 0.3246 0.04488 0.03784 0.0057 0.6247 0.9019
5.500 0.3265 0.04587 0.03890 0.0078 0.6142 0.9165
5.750 0.3638 0.04551 0.03864 0.0074 0.6076 0.9295
6.000 0.3801 0.04634 0.03957 0.0074 0.5966 0.9461
6.250 0.4351 0.04576 0.03913 0.0044 0.5899 0.9584
6.500 0.5141 0.04390 0.03742 0.0002 0.5867 0.9657
6.750 0.5493 0.04473 0.03841 -0.0036 0.5718 0.9801
7.000 0.6402 0.04091 0.03477 -0.0073 0.5684 0.9837
7.250 0.6993 0.03932 0.03335 -0.0111 0.5555 0.9937
7.500 0.8283 0.03146 0.02562 -0.0156 0.5547 0.9840
7.750 0.9096 0.02768 0.02194 -0.0201 0.5386 0.9866
8.000 0.9809 0.02467 0.01895 -0.0244 0.5167 0.9919
8.250 0.9922 0.02421 0.01862 -0.0225 0.4957 1.0000
8.500 0.9808 0.02365 0.01803 -0.0163 0.4825 1.0000
8.750 0.9694 0.02369 0.01812 -0.0111 0.4631 1.0000
9.000 0.9671 0.02382 0.01825 -0.0074 0.4322 1.0000
9.250 0.9622 0.02452 0.01879 -0.0041 0.3809 1.0000
9.500 0.9546 0.02584 0.01942 -0.0007 0.3068 1.0000
9.750 0.9375 0.02848 0.02152 0.0023 0.2521 1.0000
10.000 0.9239 0.03128 0.02389 0.0046 0.2111 1.0000
10.250 0.9172 0.03381 0.02606 0.0064 0.1797 1.0000
10.500 0.9180 0.03592 0.02784 0.0079 0.1560 1.0000
10.750 0.9258 0.03764 0.02937 0.0091 0.1373 1.0000
11.000 0.9388 0.03910 0.03066 0.0101 0.1233 1.0000
11.250 0.9571 0.04037 0.03177 0.0109 0.1123 1.0000
11.500 0.9828 0.04144 0.03257 0.0113 0.1026 1.0000
11.750 0.9991 0.04289 0.03418 0.0119 0.0963 1.0000
12.000 1.0319 0.04404 0.03513 0.0119 0.0895 1.0000
12.250 1.0487 0.04564 0.03692 0.0124 0.0850 1.0000
12.500 1.0839 0.04698 0.03809 0.0121 0.0803 1.0000
12.750 1.1012 0.04903 0.04036 0.0125 0.0771 1.0000
13.000 1.1167 0.05103 0.04255 0.0129 0.0743 1.0000
13.250 1.1368 0.05308 0.04469 0.0131 0.0720 1.0000
13.500 1.1739 0.05585 0.04740 0.0121 0.0694 1.0000
13.750 1.1688 0.05857 0.05046 0.0134 0.0688 1.0000
14.000 1.1603 0.06163 0.05385 0.0145 0.0679 1.0000
14.250 1.1515 0.06497 0.05748 0.0153 0.0672 1.0000
14.500 1.1401 0.06873 0.06155 0.0157 0.0666 1.0000
14.750 1.1256 0.07284 0.06594 0.0158 0.0662 1.0000
15.000 1.1076 0.07746 0.07083 0.0154 0.0661 1.0000
15.250 1.0849 0.08277 0.07642 0.0145 0.0661 1.0000
15.500 1.0578 0.08890 0.08282 0.0128 0.0665 1.0000
15.750 1.0264 0.09596 0.09014 0.0101 0.0669 1.0000
16.000 0.9934 0.10402 0.09843 0.0064 0.0676 1.0000
16.250 0.9603 0.11302 0.10761 0.0018 0.0684 1.0000
16.500 0.9312 0.12245 0.11717 -0.0033 0.0691 1.0000
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