NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 0012-64 (naca001264-il) Reynolds number: 200,000 Max Cl/Cd: 43.83 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001264-il-200000.txt Download as CSV file: xf-naca001264-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0012-64
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5040 0.10445 0.10068 -0.0291 1.0000 0.0915
-11.500 -0.8654 0.06388 0.05926 -0.0461 1.0000 0.0532
-11.250 -0.8838 0.06002 0.05527 -0.0434 1.0000 0.0527
-11.000 -0.9036 0.05659 0.05169 -0.0394 1.0000 0.0522
-10.750 -0.9206 0.05290 0.04777 -0.0353 1.0000 0.0516
-10.500 -0.9351 0.04923 0.04381 -0.0309 1.0000 0.0511
-10.250 -0.9460 0.04579 0.04006 -0.0264 1.0000 0.0509
-10.000 -0.9517 0.04291 0.03686 -0.0220 1.0000 0.0512
-9.750 -0.9536 0.04041 0.03403 -0.0178 1.0000 0.0518
-9.500 -0.9523 0.03811 0.03139 -0.0139 1.0000 0.0525
-9.250 -0.9475 0.03600 0.02893 -0.0103 1.0000 0.0530
-9.000 -0.9402 0.03414 0.02676 -0.0069 1.0000 0.0535
-8.750 -0.9313 0.03293 0.02524 -0.0036 1.0000 0.0541
-8.500 -0.9169 0.02995 0.02212 -0.0020 1.0000 0.0555
-8.250 -0.9009 0.02870 0.02082 -0.0002 1.0000 0.0569
-8.000 -0.8846 0.02754 0.01955 0.0017 1.0000 0.0580
-7.750 -0.8673 0.02639 0.01826 0.0036 1.0000 0.0592
-7.500 -0.8496 0.02536 0.01711 0.0054 1.0000 0.0607
-7.250 -0.8318 0.02450 0.01610 0.0072 1.0000 0.0624
-7.000 -0.8138 0.02379 0.01521 0.0090 1.0000 0.0637
-6.750 -0.7929 0.02233 0.01370 0.0101 1.0000 0.0654
-6.500 -0.7739 0.02137 0.01278 0.0116 1.0000 0.0673
-6.250 -0.7557 0.02070 0.01211 0.0132 1.0000 0.0696
-6.000 -0.7374 0.02013 0.01150 0.0149 1.0000 0.0725
-5.750 -0.7187 0.01965 0.01093 0.0165 1.0000 0.0751
-5.500 -0.7018 0.01867 0.01002 0.0183 1.0000 0.0786
-5.250 -0.6844 0.01811 0.00950 0.0201 1.0000 0.0830
-5.000 -0.6662 0.01767 0.00899 0.0218 1.0000 0.0884
-4.750 -0.6499 0.01696 0.00839 0.0236 1.0000 0.0976
-4.500 -0.6328 0.01636 0.00787 0.0253 1.0000 0.1119
-4.250 -0.6156 0.01571 0.00740 0.0270 1.0000 0.1364
-4.000 -0.5980 0.01507 0.00702 0.0284 1.0000 0.1791
-3.750 -0.5810 0.01431 0.00668 0.0298 1.0000 0.2530
-3.500 -0.5610 0.01312 0.00635 0.0303 0.9986 0.4127
-3.250 -0.5339 0.01218 0.00637 0.0301 0.9954 0.6056
-3.000 -0.5025 0.01201 0.00662 0.0297 0.9918 0.7082
-2.750 -0.4705 0.01211 0.00692 0.0293 0.9874 0.7720
-2.500 -0.4354 0.01241 0.00731 0.0284 0.9837 0.8177
-2.250 -0.4047 0.01266 0.00756 0.0283 0.9784 0.8462
-2.000 -0.3698 0.01297 0.00785 0.0273 0.9737 0.8651
-1.750 -0.3309 0.01333 0.00816 0.0254 0.9705 0.8815
-1.500 -0.3005 0.01366 0.00848 0.0254 0.9644 0.8976
-1.250 -0.2615 0.01417 0.00895 0.0240 0.9605 0.9134
-1.000 -0.2164 0.01465 0.00939 0.0211 0.9579 0.9264
-0.750 -0.1566 0.01530 0.01001 0.0153 0.9577 0.9351
-0.500 -0.1006 0.01564 0.01031 0.0097 0.9566 0.9425
-0.250 -0.0460 0.01576 0.01042 0.0040 0.9543 0.9450
0.000 0.0000 0.01579 0.01045 0.0000 0.9491 0.9491
0.250 0.0460 0.01576 0.01042 -0.0040 0.9450 0.9543
0.500 0.1006 0.01564 0.01031 -0.0097 0.9425 0.9566
0.750 0.1566 0.01530 0.01001 -0.0153 0.9351 0.9577
1.000 0.2165 0.01465 0.00939 -0.0211 0.9264 0.9579
1.250 0.2614 0.01417 0.00895 -0.0240 0.9134 0.9605
1.500 0.3004 0.01366 0.00847 -0.0254 0.8976 0.9645
1.750 0.3308 0.01333 0.00816 -0.0254 0.8815 0.9705
2.000 0.3697 0.01296 0.00784 -0.0273 0.8651 0.9738
2.250 0.4046 0.01266 0.00756 -0.0283 0.8462 0.9785
2.500 0.4354 0.01241 0.00731 -0.0284 0.8178 0.9837
2.750 0.4704 0.01211 0.00692 -0.0293 0.7720 0.9874
3.000 0.5024 0.01201 0.00662 -0.0297 0.7081 0.9918
3.250 0.5339 0.01218 0.00637 -0.0301 0.6056 0.9954
3.500 0.5610 0.01311 0.00635 -0.0303 0.4134 0.9987
3.750 0.5809 0.01430 0.00667 -0.0298 0.2533 1.0000
4.000 0.5979 0.01507 0.00701 -0.0284 0.1792 1.0000
4.250 0.6155 0.01571 0.00740 -0.0269 0.1365 1.0000
4.500 0.6327 0.01635 0.00787 -0.0253 0.1119 1.0000
4.750 0.6498 0.01696 0.00839 -0.0236 0.0976 1.0000
5.000 0.6661 0.01766 0.00898 -0.0218 0.0884 1.0000
5.250 0.6843 0.01811 0.00949 -0.0201 0.0830 1.0000
5.500 0.7017 0.01866 0.01002 -0.0183 0.0786 1.0000
5.750 0.7186 0.01965 0.01092 -0.0165 0.0751 1.0000
6.000 0.7373 0.02013 0.01149 -0.0148 0.0725 1.0000
6.250 0.7556 0.02070 0.01211 -0.0132 0.0696 1.0000
6.500 0.7738 0.02136 0.01277 -0.0115 0.0673 1.0000
6.750 0.7928 0.02232 0.01370 -0.0101 0.0654 1.0000
7.000 0.8137 0.02378 0.01521 -0.0090 0.0637 1.0000
7.250 0.8317 0.02450 0.01610 -0.0072 0.0624 1.0000
7.500 0.8495 0.02535 0.01710 -0.0053 0.0607 1.0000
7.750 0.8672 0.02638 0.01826 -0.0035 0.0592 1.0000
8.000 0.8845 0.02754 0.01954 -0.0017 0.0581 1.0000
8.250 0.9008 0.02870 0.02082 0.0002 0.0569 1.0000
8.500 0.9168 0.02995 0.02212 0.0020 0.0555 1.0000
8.750 0.9312 0.03294 0.02524 0.0036 0.0541 1.0000
9.000 0.9401 0.03413 0.02675 0.0069 0.0535 1.0000
9.250 0.9475 0.03599 0.02893 0.0103 0.0530 1.0000
9.500 0.9522 0.03811 0.03138 0.0139 0.0525 1.0000
9.750 0.9536 0.04040 0.03402 0.0178 0.0518 1.0000
10.000 0.9517 0.04291 0.03685 0.0220 0.0512 1.0000
10.250 0.9461 0.04579 0.04006 0.0264 0.0509 1.0000
10.500 0.9353 0.04923 0.04382 0.0309 0.0511 1.0000
10.750 0.9208 0.05292 0.04778 0.0352 0.0516 1.0000
11.000 0.9039 0.05662 0.05171 0.0393 0.0522 1.0000
11.250 0.8840 0.06006 0.05531 0.0433 0.0527 1.0000
11.500 0.8659 0.06394 0.05932 0.0459 0.0532 1.0000
11.750 0.7323 0.06051 0.05639 0.0535 0.0559 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 0012-64 (naca001264-il)