NACA 65(4)-421 a=0.5 (naca654421a05-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(4)-421 a=0.5 (naca654421a05-il) Reynolds number: 200,000 Max Cl/Cd: 44.44 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca654421a05-il-200000-n5.txt Download as CSV file: xf-naca654421a05-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(4)-421 a=0.5
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.6377 0.09051 0.08561 -0.0837 0.8413 0.0306
-17.000 -0.6712 0.08193 0.07675 -0.0887 0.8370 0.0307
-16.750 -0.6975 0.07527 0.06982 -0.0920 0.8324 0.0308
-16.500 -0.7175 0.06992 0.06421 -0.0943 0.8278 0.0309
-16.250 -0.7351 0.06525 0.05929 -0.0959 0.8223 0.0312
-16.000 -0.7481 0.06134 0.05512 -0.0969 0.8170 0.0313
-15.750 -0.7618 0.05778 0.05127 -0.0975 0.8122 0.0317
-15.500 -0.7720 0.05462 0.04785 -0.0977 0.8071 0.0319
-15.250 -0.7777 0.05189 0.04490 -0.0977 0.8019 0.0322
-15.000 -0.7695 0.05007 0.04298 -0.0976 0.7971 0.0324
-14.750 -0.7618 0.04839 0.04120 -0.0973 0.7929 0.0328
-14.500 -0.7542 0.04677 0.03949 -0.0972 0.7882 0.0331
-14.250 -0.7464 0.04517 0.03779 -0.0969 0.7834 0.0335
-14.000 -0.7390 0.04368 0.03618 -0.0965 0.7789 0.0340
-13.750 -0.7302 0.04218 0.03452 -0.0959 0.7748 0.0344
-13.500 -0.7201 0.04080 0.03299 -0.0954 0.7706 0.0349
-13.250 -0.7078 0.03944 0.03150 -0.0950 0.7660 0.0353
-13.000 -0.6949 0.03819 0.03009 -0.0944 0.7616 0.0357
-12.750 -0.6813 0.03701 0.02875 -0.0938 0.7578 0.0362
-12.500 -0.6689 0.03593 0.02746 -0.0931 0.7546 0.0367
-12.250 -0.6491 0.03493 0.02641 -0.0929 0.7508 0.0372
-12.000 -0.6286 0.03404 0.02552 -0.0926 0.7470 0.0376
-11.750 -0.6098 0.03317 0.02463 -0.0922 0.7434 0.0382
-11.500 -0.5918 0.03234 0.02375 -0.0917 0.7400 0.0386
-11.250 -0.5743 0.03154 0.02287 -0.0911 0.7370 0.0391
-11.000 -0.5567 0.03075 0.02202 -0.0906 0.7338 0.0396
-10.750 -0.5393 0.02996 0.02120 -0.0900 0.7300 0.0401
-10.500 -0.5226 0.02919 0.02037 -0.0894 0.7263 0.0407
-10.250 -0.5062 0.02843 0.01954 -0.0886 0.7231 0.0413
-10.000 -0.4903 0.02771 0.01873 -0.0879 0.7203 0.0420
-9.750 -0.4761 0.02691 0.01788 -0.0869 0.7178 0.0428
-9.500 -0.4628 0.02608 0.01705 -0.0859 0.7150 0.0435
-9.250 -0.4487 0.02533 0.01631 -0.0850 0.7119 0.0444
-9.000 -0.4351 0.02459 0.01554 -0.0840 0.7089 0.0453
-8.750 -0.4218 0.02387 0.01477 -0.0828 0.7059 0.0462
-8.500 -0.4082 0.02319 0.01403 -0.0816 0.7032 0.0471
-8.250 -0.3946 0.02255 0.01329 -0.0803 0.7007 0.0482
-8.000 -0.3832 0.02183 0.01253 -0.0788 0.6983 0.0494
-7.750 -0.3705 0.02121 0.01190 -0.0773 0.6954 0.0509
-7.500 -0.3568 0.02066 0.01134 -0.0759 0.6925 0.0527
-7.250 -0.3432 0.02019 0.01081 -0.0743 0.6899 0.0548
-7.000 -0.3323 0.01972 0.01035 -0.0722 0.6874 0.0577
-6.750 -0.3205 0.01935 0.00994 -0.0700 0.6852 0.0622
-6.500 -0.3082 0.01893 0.00953 -0.0680 0.6831 0.0694
-6.250 -0.2948 0.01846 0.00909 -0.0661 0.6813 0.0834
-6.000 -0.2829 0.01790 0.00868 -0.0641 0.6791 0.1117
-5.750 -0.2719 0.01728 0.00830 -0.0620 0.6764 0.1579
-5.500 -0.2611 0.01660 0.00790 -0.0599 0.6737 0.2138
-5.250 -0.2520 0.01580 0.00745 -0.0574 0.6712 0.2894
-5.000 -0.2440 0.01494 0.00707 -0.0547 0.6691 0.3880
-4.750 -0.2276 0.01458 0.00707 -0.0530 0.6671 0.4755
-4.500 -0.2037 0.01453 0.00706 -0.0524 0.6654 0.5142
-4.250 -0.1789 0.01456 0.00711 -0.0519 0.6639 0.5438
-4.000 -0.1534 0.01465 0.00713 -0.0515 0.6624 0.5681
-3.750 -0.1287 0.01480 0.00731 -0.0511 0.6602 0.5864
-3.500 -0.1035 0.01500 0.00754 -0.0506 0.6577 0.6037
-3.250 -0.0775 0.01521 0.00780 -0.0502 0.6554 0.6184
-3.000 -0.0512 0.01530 0.00784 -0.0500 0.6532 0.6278
-2.750 -0.0235 0.01535 0.00786 -0.0501 0.6514 0.6323
-2.500 0.0042 0.01535 0.00779 -0.0503 0.6497 0.6363
-2.250 0.0318 0.01533 0.00769 -0.0506 0.6482 0.6401
-2.000 0.0595 0.01531 0.00756 -0.0508 0.6468 0.6441
-1.750 0.0883 0.01530 0.00751 -0.0512 0.6454 0.6467
-1.500 0.1157 0.01535 0.00754 -0.0514 0.6437 0.6494
-1.250 0.1411 0.01545 0.00766 -0.0513 0.6413 0.6527
-1.000 0.1671 0.01553 0.00774 -0.0513 0.6389 0.6565
-0.750 0.1934 0.01559 0.00777 -0.0514 0.6369 0.6602
-0.500 0.2201 0.01565 0.00778 -0.0516 0.6351 0.6638
-0.250 0.2474 0.01570 0.00785 -0.0518 0.6334 0.6664
0.000 0.2750 0.01575 0.00790 -0.0520 0.6319 0.6695
0.250 0.3029 0.01580 0.00792 -0.0522 0.6304 0.6732
0.500 0.3314 0.01582 0.00791 -0.0526 0.6290 0.6772
0.750 0.3604 0.01585 0.00789 -0.0531 0.6276 0.6812
1.000 0.3850 0.01601 0.00809 -0.0529 0.6256 0.6846
1.250 0.4076 0.01624 0.00840 -0.0525 0.6233 0.6878
1.500 0.4311 0.01644 0.00866 -0.0521 0.6210 0.6914
1.750 0.4554 0.01662 0.00886 -0.0519 0.6189 0.6957
2.000 0.4808 0.01674 0.00900 -0.0519 0.6168 0.7005
2.250 0.5074 0.01683 0.00910 -0.0519 0.6150 0.7046
2.500 0.5346 0.01691 0.00922 -0.0521 0.6135 0.7084
2.750 0.5625 0.01699 0.00933 -0.0524 0.6122 0.7127
3.000 0.5914 0.01707 0.00940 -0.0529 0.6109 0.7174
3.250 0.6206 0.01715 0.00948 -0.0534 0.6096 0.7223
3.500 0.6313 0.01768 0.01017 -0.0511 0.6058 0.7265
3.750 0.6480 0.01806 0.01066 -0.0497 0.6029 0.7315
4.000 0.6684 0.01834 0.01100 -0.0489 0.6005 0.7373
4.250 0.6922 0.01850 0.01120 -0.0486 0.5983 0.7431
4.500 0.7180 0.01859 0.01136 -0.0485 0.5965 0.7480
4.750 0.7464 0.01864 0.01147 -0.0489 0.5951 0.7534
5.000 0.7771 0.01866 0.01151 -0.0496 0.5937 0.7594
5.250 0.7976 0.01894 0.01186 -0.0488 0.5914 0.7650
5.500 0.7779 0.02007 0.01320 -0.0418 0.5848 0.7725
5.750 0.7916 0.02035 0.01354 -0.0399 0.5817 0.7802
6.000 0.8173 0.02036 0.01362 -0.0397 0.5796 0.7867
6.250 0.8505 0.02021 0.01354 -0.0407 0.5780 0.7935
6.500 0.8892 0.02001 0.01338 -0.0426 0.5766 0.8007
7.000 0.8500 0.02250 0.01611 -0.0295 0.5628 0.8224
7.250 0.8896 0.02185 0.01554 -0.0310 0.5612 0.8295
7.500 0.9343 0.02111 0.01484 -0.0332 0.5596 0.8375
7.750 0.8689 0.02460 0.01851 -0.0221 0.5464 0.8569
8.000 0.9113 0.02358 0.01756 -0.0236 0.5446 0.8662
8.500 0.9122 0.02582 0.02003 -0.0182 0.5292 0.9020
8.750 0.9530 0.02490 0.01918 -0.0196 0.5261 0.9176
9.000 0.9480 0.02758 0.02204 -0.0190 0.5133 0.9535
9.250 0.9461 0.02976 0.02431 -0.0180 0.5004 1.0000
9.500 0.9615 0.03025 0.02481 -0.0173 0.4897 1.0000
9.750 0.9762 0.03071 0.02527 -0.0164 0.4747 1.0000
10.000 0.9899 0.03124 0.02576 -0.0154 0.4550 1.0000
10.250 1.0199 0.03042 0.02477 -0.0153 0.4255 1.0000
10.500 1.0371 0.03042 0.02444 -0.0140 0.3830 1.0000
10.750 1.0354 0.03207 0.02582 -0.0119 0.3463 1.0000
11.000 1.0294 0.03421 0.02774 -0.0096 0.3140 1.0000
11.250 1.0229 0.03657 0.02991 -0.0076 0.2846 1.0000
11.500 1.0171 0.03899 0.03217 -0.0059 0.2562 1.0000
11.750 1.0133 0.04139 0.03443 -0.0044 0.2308 1.0000
12.000 1.0091 0.04390 0.03678 -0.0031 0.2045 1.0000
12.250 1.0069 0.04633 0.03908 -0.0020 0.1804 1.0000
12.500 1.0058 0.04875 0.04136 -0.0010 0.1579 1.0000
12.750 1.0045 0.05124 0.04372 -0.0002 0.1340 1.0000
13.000 1.0049 0.05364 0.04599 0.0005 0.1125 1.0000
13.250 1.0042 0.05619 0.04841 0.0011 0.0907 1.0000
13.500 1.0062 0.05856 0.05067 0.0016 0.0737 1.0000
13.750 1.0074 0.06105 0.05307 0.0021 0.0582 1.0000
14.250 1.0149 0.06568 0.05762 0.0026 0.0433 1.0000
14.500 1.0200 0.06796 0.05992 0.0027 0.0393 1.0000
14.750 1.0250 0.07027 0.06225 0.0027 0.0371 1.0000
15.000 1.0305 0.07256 0.06460 0.0027 0.0345 1.0000
15.250 1.0340 0.07510 0.06717 0.0026 0.0329 1.0000
15.500 1.0396 0.07747 0.06960 0.0025 0.0316 1.0000
15.750 1.0443 0.07997 0.07217 0.0023 0.0302 1.0000
16.000 1.0486 0.08256 0.07483 0.0020 0.0294 1.0000
16.250 1.0512 0.08538 0.07769 0.0016 0.0286 1.0000
16.500 1.0540 0.08819 0.08057 0.0012 0.0278 1.0000
16.750 1.0584 0.09084 0.08330 0.0008 0.0273 1.0000
17.000 1.0623 0.09358 0.08612 0.0003 0.0267 1.0000
17.250 1.0665 0.09631 0.08892 -0.0003 0.0260 1.0000
17.500 1.0695 0.09920 0.09186 -0.0010 0.0254 1.0000
17.750 1.0736 0.10193 0.09465 -0.0017 0.0250 1.0000
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