NACA CYH (nacacyh-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA CYH (nacacyh-il) Reynolds number: 200,000 Max Cl/Cd: 65.44 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacacyh-il-200000.txt Download as CSV file: xf-nacacyh-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA CYH
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4515 0.09208 0.08863 -0.0202 1.0000 0.0725
-9.750 -0.4751 0.08476 0.08140 -0.0328 1.0000 0.0761
-9.500 -0.5133 0.07744 0.07388 -0.0427 1.0000 0.0768
-9.250 -0.5052 0.07174 0.06831 -0.0419 1.0000 0.0781
-9.000 -0.4865 0.07057 0.06723 -0.0389 1.0000 0.0794
-8.750 -0.4775 0.06829 0.06497 -0.0380 1.0000 0.0811
-8.500 -0.4751 0.06513 0.06181 -0.0384 1.0000 0.0831
-8.250 -0.4825 0.06192 0.05858 -0.0378 1.0000 0.0855
-8.000 -0.4984 0.05444 0.05058 -0.0423 0.9905 0.0917
-7.750 -0.4658 0.05123 0.04745 -0.0449 0.9849 0.0934
-7.500 -0.4339 0.04845 0.04460 -0.0478 0.9775 0.0971
-7.250 -0.4282 0.03175 0.02602 -0.0501 0.9623 0.0630
-7.000 -0.3979 0.02802 0.02185 -0.0515 0.9545 0.0612
-6.750 -0.3700 0.02564 0.01906 -0.0517 0.9430 0.0614
-6.500 -0.3422 0.02381 0.01689 -0.0516 0.9317 0.0620
-6.250 -0.3144 0.02214 0.01490 -0.0513 0.9217 0.0621
-6.000 -0.2883 0.02084 0.01334 -0.0506 0.9106 0.0626
-5.750 -0.2625 0.01979 0.01207 -0.0498 0.8995 0.0633
-5.500 -0.2364 0.01906 0.01114 -0.0489 0.8901 0.0645
-5.250 -0.2112 0.01787 0.00986 -0.0481 0.8799 0.0664
-5.000 -0.1858 0.01707 0.00904 -0.0474 0.8706 0.0683
-4.750 -0.1603 0.01645 0.00837 -0.0465 0.8618 0.0704
-4.500 -0.1348 0.01591 0.00779 -0.0458 0.8523 0.0731
-4.000 -0.0857 0.01479 0.00661 -0.0438 0.8330 0.0814
-3.750 -0.0607 0.01444 0.00621 -0.0428 0.8233 0.0896
-3.500 -0.0373 0.01379 0.00563 -0.0417 0.8136 0.1071
-3.250 -0.0146 0.01303 0.00522 -0.0406 0.8036 0.1695
-3.000 0.0080 0.01246 0.00502 -0.0395 0.7948 0.2710
-2.750 0.0305 0.01195 0.00488 -0.0385 0.7843 0.3670
-2.500 0.0486 0.01113 0.00472 -0.0365 0.7761 0.5328
-2.250 0.0799 0.01049 0.00525 -0.0350 0.7682 0.8956
-2.000 0.1317 0.01095 0.00557 -0.0382 0.7612 0.9538
-1.750 0.2122 0.01122 0.00564 -0.0482 0.7521 0.9850
-1.500 0.2747 0.01118 0.00543 -0.0552 0.7434 1.0000
-1.250 0.3002 0.01117 0.00531 -0.0548 0.7343 1.0000
-1.000 0.3259 0.01117 0.00522 -0.0545 0.7257 1.0000
-0.750 0.3514 0.01117 0.00511 -0.0540 0.7168 1.0000
-0.500 0.3770 0.01117 0.00505 -0.0537 0.7069 1.0000
0.000 0.4280 0.01118 0.00490 -0.0528 0.6875 1.0000
0.250 0.4535 0.01119 0.00485 -0.0523 0.6780 1.0000
0.500 0.4788 0.01119 0.00478 -0.0518 0.6680 1.0000
0.750 0.5039 0.01120 0.00476 -0.0514 0.6566 1.0000
1.000 0.5288 0.01121 0.00471 -0.0508 0.6454 1.0000
1.250 0.5537 0.01122 0.00464 -0.0502 0.6338 1.0000
1.500 0.5783 0.01123 0.00462 -0.0496 0.6204 1.0000
1.750 0.6028 0.01126 0.00461 -0.0490 0.6063 1.0000
2.000 0.6271 0.01130 0.00461 -0.0483 0.5912 1.0000
2.250 0.6512 0.01137 0.00461 -0.0476 0.5748 1.0000
2.500 0.6750 0.01146 0.00462 -0.0469 0.5573 1.0000
2.750 0.6986 0.01160 0.00469 -0.0461 0.5386 1.0000
3.000 0.7219 0.01177 0.00480 -0.0454 0.5192 1.0000
3.250 0.7450 0.01197 0.00491 -0.0446 0.5001 1.0000
3.500 0.7677 0.01221 0.00505 -0.0438 0.4819 1.0000
3.750 0.7904 0.01246 0.00521 -0.0430 0.4653 1.0000
4.000 0.8132 0.01272 0.00542 -0.0422 0.4505 1.0000
4.250 0.8356 0.01298 0.00564 -0.0414 0.4359 1.0000
4.500 0.8578 0.01325 0.00585 -0.0405 0.4214 1.0000
4.750 0.8799 0.01353 0.00610 -0.0397 0.4082 1.0000
5.000 0.9022 0.01385 0.00636 -0.0389 0.3974 1.0000
5.250 0.9245 0.01417 0.00666 -0.0381 0.3871 1.0000
5.500 0.9469 0.01447 0.00699 -0.0373 0.3768 1.0000
5.750 0.9690 0.01483 0.00731 -0.0366 0.3675 1.0000
6.000 0.9910 0.01515 0.00767 -0.0358 0.3578 1.0000
6.250 1.0128 0.01549 0.00804 -0.0350 0.3480 1.0000
6.500 1.0344 0.01590 0.00840 -0.0342 0.3382 1.0000
6.750 1.0556 0.01619 0.00878 -0.0333 0.3272 1.0000
7.000 1.0767 0.01655 0.00920 -0.0324 0.3163 1.0000
7.250 1.0971 0.01692 0.00958 -0.0315 0.3043 1.0000
7.500 1.1166 0.01725 0.00994 -0.0304 0.2899 1.0000
7.750 1.1356 0.01755 0.01031 -0.0293 0.2725 1.0000
8.000 1.1541 0.01789 0.01070 -0.0282 0.2523 1.0000
8.250 1.1712 0.01835 0.01114 -0.0269 0.2299 1.0000
8.500 1.1864 0.01898 0.01169 -0.0255 0.2043 1.0000
8.750 1.1997 0.01980 0.01241 -0.0238 0.1816 1.0000
9.000 1.2115 0.02073 0.01326 -0.0220 0.1649 1.0000
9.250 1.2233 0.02165 0.01416 -0.0203 0.1523 1.0000
9.500 1.2336 0.02257 0.01507 -0.0183 0.1423 1.0000
9.750 1.2408 0.02359 0.01604 -0.0160 0.1335 1.0000
10.000 1.2531 0.02441 0.01696 -0.0145 0.1253 1.0000
10.250 1.2612 0.02551 0.01808 -0.0129 0.1180 1.0000
10.500 1.2717 0.02653 0.01916 -0.0117 0.1093 1.0000
10.750 1.2818 0.02767 0.02037 -0.0106 0.1014 1.0000
11.000 1.2879 0.02915 0.02186 -0.0095 0.0931 1.0000
11.250 1.2941 0.03075 0.02351 -0.0086 0.0821 1.0000
11.500 1.2995 0.03256 0.02535 -0.0079 0.0661 1.0000
11.750 1.2977 0.03510 0.02784 -0.0071 0.0521 1.0000
12.000 1.2951 0.03783 0.03056 -0.0064 0.0442 1.0000
12.250 1.2922 0.04069 0.03346 -0.0060 0.0400 1.0000
12.500 1.2890 0.04367 0.03650 -0.0058 0.0372 1.0000
13.000 1.2783 0.05038 0.04339 -0.0059 0.0341 1.0000
13.250 1.2740 0.05376 0.04689 -0.0061 0.0330 1.0000
13.500 1.2686 0.05733 0.05056 -0.0065 0.0320 1.0000
13.750 1.2626 0.06110 0.05443 -0.0071 0.0312 1.0000
14.000 1.2555 0.06511 0.05851 -0.0078 0.0305 1.0000
14.250 1.2478 0.06923 0.06268 -0.0086 0.0298 1.0000
14.500 1.2431 0.07300 0.06654 -0.0092 0.0292 1.0000
14.750 1.2407 0.07661 0.07028 -0.0100 0.0286 1.0000
15.000 1.2382 0.08028 0.07406 -0.0108 0.0279 1.0000
15.250 1.2357 0.08399 0.07787 -0.0117 0.0273 1.0000
15.500 1.2335 0.08770 0.08167 -0.0127 0.0266 1.0000
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Polar data table (+)
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