NACA 65(3)-218 (naca653218-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(3)-218 (naca653218-il) Reynolds number: 50,000 Max Cl/Cd: 17.07 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca653218-il-50000-n5.txt Download as CSV file: xf-naca653218-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6131 0.09823 0.09026 -0.0644 1.0000 0.0602
-14.000 -0.6369 0.09143 0.08335 -0.0678 1.0000 0.0599
-13.750 -0.6637 0.08514 0.07692 -0.0705 1.0000 0.0598
-13.500 -0.6864 0.07985 0.07147 -0.0723 1.0000 0.0597
-13.250 -0.7097 0.07507 0.06649 -0.0732 1.0000 0.0597
-13.000 -0.7303 0.07096 0.06217 -0.0734 1.0000 0.0599
-12.750 -0.7488 0.06735 0.05832 -0.0729 1.0000 0.0601
-12.500 -0.7629 0.06421 0.05497 -0.0719 1.0000 0.0603
-12.250 -0.7595 0.06172 0.05242 -0.0712 1.0000 0.0612
-12.000 -0.7596 0.05934 0.04993 -0.0700 1.0000 0.0619
-11.750 -0.7598 0.05720 0.04767 -0.0685 1.0000 0.0627
-11.500 -0.7597 0.05524 0.04558 -0.0666 1.0000 0.0634
-11.250 -0.7606 0.05355 0.04376 -0.0641 1.0000 0.0640
-11.000 -0.7628 0.05216 0.04225 -0.0610 1.0000 0.0647
-10.750 -0.7664 0.05105 0.04103 -0.0574 1.0000 0.0654
-10.500 -0.7695 0.05009 0.03995 -0.0537 1.0000 0.0662
-10.250 -0.7723 0.04924 0.03894 -0.0500 1.0000 0.0673
-10.000 -0.7413 0.04748 0.03682 -0.0513 0.9947 0.0702
-9.750 -0.6902 0.04616 0.03558 -0.0539 0.9915 0.0740
-9.500 -0.6396 0.04535 0.03460 -0.0557 0.9877 0.0785
-9.250 -0.5980 0.04457 0.03377 -0.0573 0.9830 0.0841
-9.000 -0.5660 0.04367 0.03281 -0.0586 0.9762 0.0904
-8.750 -0.5372 0.04258 0.03171 -0.0598 0.9698 0.0973
-8.500 -0.5126 0.04133 0.03044 -0.0611 0.9625 0.1076
-8.250 -0.4941 0.03980 0.02901 -0.0621 0.9549 0.1216
-8.000 -0.4794 0.03790 0.02734 -0.0632 0.9475 0.1429
-7.750 -0.4751 0.03599 0.02575 -0.0628 0.9378 0.1786
-7.500 -0.4767 0.03380 0.02414 -0.0618 0.9288 0.2455
-7.250 -0.4464 0.03543 0.02717 -0.0581 0.9226 0.4212
-7.000 -0.4247 0.03606 0.02768 -0.0571 0.9157 0.4899
-6.750 -0.4308 0.03592 0.02742 -0.0531 0.9041 0.5250
-6.500 -0.3993 0.03862 0.02995 -0.0504 0.8987 0.5694
-6.250 -0.4072 0.03899 0.03022 -0.0450 0.8877 0.5933
-6.000 -0.3488 0.04158 0.03252 -0.0458 0.8853 0.6135
-5.750 -0.3266 0.04184 0.03257 -0.0448 0.8799 0.6288
-5.500 -0.2846 0.04272 0.03321 -0.0456 0.8749 0.6376
-5.250 -0.2674 0.04264 0.03296 -0.0443 0.8685 0.6490
-5.000 -0.2698 0.04224 0.03245 -0.0406 0.8610 0.6622
-4.750 -0.2299 0.04259 0.03260 -0.0419 0.8564 0.6673
-4.500 -0.2341 0.04205 0.03197 -0.0382 0.8495 0.6796
-4.250 -0.1865 0.04206 0.03177 -0.0411 0.8471 0.6839
-4.000 -0.1844 0.04215 0.03180 -0.0375 0.8388 0.6916
-3.750 -0.1751 0.04180 0.03133 -0.0354 0.8331 0.6999
-3.500 -0.1403 0.04163 0.03101 -0.0369 0.8301 0.7049
-3.250 -0.1690 0.04146 0.03084 -0.0293 0.8206 0.7155
-3.000 -0.1372 0.04144 0.03070 -0.0301 0.8167 0.7194
-2.750 -0.1107 0.04120 0.03034 -0.0305 0.8132 0.7247
-2.500 -0.1361 0.04104 0.03016 -0.0232 0.8047 0.7338
-2.250 -0.1131 0.04108 0.03013 -0.0229 0.8003 0.7377
-2.000 -0.0920 0.04088 0.02984 -0.0225 0.7967 0.7427
-1.750 -0.1083 0.04058 0.02951 -0.0167 0.7900 0.7512
-1.500 -0.0954 0.04075 0.02963 -0.0148 0.7843 0.7550
-1.250 -0.0774 0.04067 0.02949 -0.0140 0.7804 0.7597
-1.000 -0.0656 0.04027 0.02901 -0.0124 0.7771 0.7663
-0.750 -0.0773 0.04052 0.02927 -0.0070 0.7695 0.7717
-0.500 -0.0635 0.04056 0.02927 -0.0054 0.7648 0.7761
-0.250 -0.0476 0.04041 0.02907 -0.0044 0.7614 0.7816
0.000 -0.0380 0.04027 0.02888 -0.0024 0.7574 0.7874
0.250 -0.0441 0.04060 0.02923 0.0021 0.7503 0.7923
0.500 -0.0280 0.04062 0.02922 0.0031 0.7462 0.7974
0.750 -0.0109 0.04044 0.02899 0.0038 0.7431 0.8037
1.000 -0.0015 0.04079 0.02936 0.0059 0.7379 0.8079
1.250 0.0046 0.04106 0.02963 0.0083 0.7322 0.8132
1.500 0.0217 0.04109 0.02963 0.0090 0.7282 0.8193
1.750 0.0496 0.04121 0.02976 0.0084 0.7254 0.8236
2.000 0.0534 0.04167 0.03024 0.0110 0.7192 0.8293
2.250 0.0635 0.04190 0.03048 0.0126 0.7139 0.8358
2.500 0.0871 0.04209 0.03069 0.0125 0.7101 0.8407
2.750 0.1183 0.04227 0.03091 0.0116 0.7073 0.8453
3.000 0.1123 0.04283 0.03150 0.0151 0.6993 0.8536
3.250 0.1341 0.04315 0.03188 0.0153 0.6946 0.8589
3.500 0.1639 0.04335 0.03214 0.0146 0.6911 0.8642
3.750 0.1669 0.04391 0.03274 0.0168 0.6837 0.8725
4.000 0.1886 0.04431 0.03322 0.0170 0.6780 0.8785
4.250 0.2183 0.04451 0.03349 0.0162 0.6741 0.8853
4.500 0.2255 0.04519 0.03425 0.0178 0.6660 0.8933
4.750 0.2494 0.04555 0.03470 0.0176 0.6602 0.9008
5.000 0.2843 0.04570 0.03498 0.0162 0.6564 0.9076
5.250 0.2897 0.04656 0.03593 0.0176 0.6462 0.9178
5.500 0.3250 0.04680 0.03631 0.0160 0.6411 0.9251
5.750 0.3406 0.04757 0.03722 0.0160 0.6318 0.9355
6.000 0.3774 0.04791 0.03772 0.0138 0.6253 0.9429
6.250 0.4028 0.04865 0.03863 0.0123 0.6159 0.9523
6.750 0.4691 0.04971 0.04008 0.0077 0.5973 0.9709
7.000 0.5169 0.04949 0.04011 0.0046 0.5904 0.9790
7.250 0.5409 0.05013 0.04094 0.0031 0.5769 0.9964
7.500 0.5455 0.05022 0.04109 0.0055 0.5654 1.0000
7.750 0.5752 0.04939 0.04043 0.0060 0.5573 1.0000
8.000 0.5839 0.04971 0.04083 0.0075 0.5430 1.0000
8.250 0.5993 0.04981 0.04107 0.0085 0.5285 1.0000
8.500 0.6193 0.04954 0.04094 0.0094 0.5132 1.0000
8.750 0.6447 0.04850 0.04009 0.0105 0.4957 1.0000
9.000 0.6654 0.04724 0.03897 0.0123 0.4714 1.0000
9.250 0.6798 0.04629 0.03811 0.0144 0.4383 1.0000
9.500 0.6991 0.04514 0.03699 0.0163 0.3933 1.0000
9.750 0.7321 0.04288 0.03437 0.0186 0.3207 1.0000
10.000 0.7411 0.04353 0.03435 0.0207 0.2439 1.0000
10.250 0.7373 0.04589 0.03622 0.0221 0.1921 1.0000
10.500 0.7331 0.04857 0.03849 0.0231 0.1561 1.0000
10.750 0.7333 0.05107 0.04076 0.0238 0.1310 1.0000
11.000 0.7361 0.05343 0.04292 0.0244 0.1146 1.0000
11.250 0.7427 0.05551 0.04489 0.0249 0.1027 1.0000
11.500 0.7521 0.05735 0.04667 0.0254 0.0946 1.0000
11.750 0.7636 0.05903 0.04832 0.0258 0.0880 1.0000
12.000 0.7784 0.06049 0.04983 0.0263 0.0820 1.0000
12.250 0.7954 0.06180 0.05115 0.0268 0.0772 1.0000
12.500 0.8177 0.06278 0.05212 0.0274 0.0734 1.0000
12.750 0.8407 0.06392 0.05346 0.0278 0.0692 1.0000
13.000 0.8635 0.06506 0.05464 0.0281 0.0658 1.0000
13.250 0.8926 0.06622 0.05588 0.0285 0.0633 1.0000
13.500 0.9123 0.06828 0.05824 0.0287 0.0615 1.0000
13.750 0.9257 0.07076 0.06096 0.0287 0.0598 1.0000
14.000 0.9343 0.07344 0.06384 0.0287 0.0582 1.0000
14.250 0.9430 0.07605 0.06656 0.0285 0.0566 1.0000
14.500 0.9557 0.07862 0.06915 0.0283 0.0554 1.0000
14.750 0.9453 0.08301 0.07389 0.0277 0.0548 1.0000
15.000 0.9328 0.08780 0.07900 0.0267 0.0545 1.0000
15.250 0.9184 0.09303 0.08452 0.0252 0.0544 1.0000
15.500 0.8998 0.09902 0.09078 0.0230 0.0543 1.0000
15.750 0.8772 0.10596 0.09796 0.0199 0.0544 1.0000
16.000 0.8515 0.11403 0.10625 0.0157 0.0546 1.0000
16.250 0.8239 0.12332 0.11572 0.0105 0.0549 1.0000
16.500 0.7990 0.13323 0.12575 0.0046 0.0552 1.0000
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