NACA 65(1)-212 a=0.6 (naca651212a06-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(1)-212 a=0.6 (naca651212a06-il) Reynolds number: 100,000 Max Cl/Cd: 46.71 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca651212a06-il-100000.txt Download as CSV file: xf-naca651212a06-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-212 a=0.6
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4851 0.09496 0.09021 -0.0337 1.0000 0.1349
-9.500 -0.4912 0.09128 0.08660 -0.0364 1.0000 0.1427
-9.250 -0.5285 0.08513 0.08059 -0.0451 1.0000 0.1443
-9.000 -0.4954 0.08349 0.07892 -0.0395 1.0000 0.1566
-8.750 -0.5330 0.07803 0.07360 -0.0457 1.0000 0.1584
-8.500 -0.5131 0.07540 0.07100 -0.0432 1.0000 0.1698
-8.250 -0.5505 0.07277 0.06850 -0.0423 1.0000 0.1717
-8.000 -0.5822 0.07145 0.06725 -0.0376 1.0000 0.1715
-7.750 -0.6158 0.07021 0.06602 -0.0329 1.0000 0.1722
-7.500 -0.6582 0.06917 0.06484 -0.0287 1.0000 0.1741
-6.000 -0.5979 0.03949 0.03208 -0.0287 0.9808 0.0853
-5.750 -0.5721 0.03547 0.02766 -0.0290 0.9762 0.0785
-5.500 -0.5399 0.03284 0.02452 -0.0300 0.9721 0.0779
-5.250 -0.5106 0.03072 0.02191 -0.0302 0.9674 0.0768
-5.000 -0.4801 0.02889 0.01969 -0.0305 0.9627 0.0758
-4.750 -0.4450 0.02725 0.01786 -0.0318 0.9592 0.0768
-4.500 -0.4120 0.02609 0.01659 -0.0330 0.9554 0.0808
-4.250 -0.3861 0.02524 0.01562 -0.0327 0.9500 0.0850
-4.000 -0.3531 0.02404 0.01443 -0.0337 0.9460 0.0887
-3.750 -0.3192 0.02308 0.01358 -0.0352 0.9427 0.0967
-3.500 -0.3056 0.02251 0.01305 -0.0330 0.9365 0.1063
-3.250 -0.2790 0.02178 0.01237 -0.0331 0.9317 0.1257
-3.000 -0.2709 0.01896 0.01203 -0.0303 0.9276 0.5723
-2.750 -0.2699 0.01936 0.01284 -0.0233 0.9209 0.7220
-2.500 -0.2507 0.01977 0.01320 -0.0202 0.9163 0.7831
-2.250 -0.2284 0.02053 0.01413 -0.0159 0.9128 0.8362
-2.000 -0.2140 0.02232 0.01592 -0.0092 0.9076 0.8856
-1.750 -0.1561 0.02335 0.01672 -0.0127 0.9057 0.9207
-1.500 -0.1088 0.02345 0.01664 -0.0171 0.9025 0.9299
-1.250 -0.0457 0.02358 0.01658 -0.0246 0.9006 0.9342
-1.000 -0.0063 0.02366 0.01653 -0.0279 0.8965 0.9426
-0.750 0.0407 0.02375 0.01653 -0.0327 0.8926 0.9486
-0.500 0.0834 0.02382 0.01651 -0.0366 0.8887 0.9564
-0.250 0.1437 0.02384 0.01646 -0.0438 0.8864 0.9603
0.000 0.2009 0.02385 0.01641 -0.0502 0.8843 0.9653
0.250 0.2298 0.02406 0.01662 -0.0522 0.8781 0.9753
0.500 0.2753 0.02415 0.01671 -0.0568 0.8741 0.9830
0.750 0.3313 0.02409 0.01667 -0.0632 0.8714 0.9880
1.000 0.3854 0.02402 0.01664 -0.0690 0.8690 0.9935
1.250 0.3953 0.02451 0.01716 -0.0681 0.8605 1.0000
1.500 0.4177 0.02467 0.01737 -0.0682 0.8555 1.0000
1.750 0.3792 0.02541 0.01806 -0.0585 0.8443 1.0000
2.000 0.4093 0.02557 0.01827 -0.0597 0.8399 1.0000
2.250 0.3666 0.02626 0.01887 -0.0488 0.8282 1.0000
2.500 0.4121 0.02645 0.01913 -0.0522 0.8243 1.0000
2.750 0.3876 0.02714 0.01976 -0.0440 0.8129 1.0000
3.000 0.4379 0.02730 0.02003 -0.0480 0.8089 1.0000
3.250 0.4215 0.02806 0.02075 -0.0412 0.7977 1.0000
3.750 0.4675 0.02888 0.02173 -0.0401 0.7818 1.0000
4.000 0.4881 0.02929 0.02223 -0.0390 0.7723 1.0000
4.250 0.5379 0.02905 0.02220 -0.0421 0.7648 1.0000
4.500 0.6282 0.02571 0.01920 -0.0470 0.7463 1.0000
4.750 0.7072 0.01894 0.01256 -0.0448 0.6992 1.0000
5.000 0.7308 0.01742 0.01113 -0.0412 0.6676 1.0000
5.250 0.7455 0.01596 0.00966 -0.0358 0.5953 1.0000
5.500 0.7244 0.01733 0.00909 -0.0259 0.2696 1.0000
5.750 0.7091 0.01995 0.01053 -0.0197 0.1300 1.0000
6.000 0.7146 0.02131 0.01168 -0.0162 0.1051 1.0000
6.250 0.7234 0.02254 0.01284 -0.0132 0.0944 1.0000
6.500 0.7352 0.02385 0.01400 -0.0108 0.0857 1.0000
6.750 0.7550 0.02500 0.01517 -0.0095 0.0787 1.0000
7.000 0.7817 0.02652 0.01658 -0.0092 0.0740 1.0000
7.250 0.8202 0.02893 0.01893 -0.0105 0.0707 1.0000
7.500 0.8484 0.03045 0.02067 -0.0101 0.0676 1.0000
7.750 0.8765 0.03232 0.02271 -0.0100 0.0648 1.0000
8.000 0.9043 0.03471 0.02537 -0.0096 0.0642 1.0000
8.250 0.9282 0.03743 0.02849 -0.0087 0.0647 1.0000
8.500 0.9484 0.04057 0.03205 -0.0074 0.0663 1.0000
8.750 0.9646 0.04391 0.03578 -0.0058 0.0677 1.0000
9.000 0.9768 0.04728 0.03952 -0.0040 0.0684 1.0000
9.250 0.9873 0.05109 0.04363 -0.0023 0.0696 1.0000
9.500 0.9840 0.05590 0.04927 0.0018 0.0806 1.0000
11.500 0.7208 0.11706 0.11214 -0.0122 0.1745 1.0000
11.750 0.7390 0.12058 0.11569 -0.0105 0.1686 1.0000
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Polar data table (+)
Polar graphs
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