NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63-209 (naca63209-il) Reynolds number: 50,000 Max Cl/Cd: 32.91 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca63209-il-50000-n5.txt Download as CSV file: xf-naca63209-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63-209
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5624 0.09658 0.08957 -0.0169 1.0000 0.0530
-9.250 -0.5635 0.09164 0.08469 -0.0197 1.0000 0.0522
-9.000 -0.5666 0.08624 0.07934 -0.0234 1.0000 0.0515
-8.750 -0.5734 0.08043 0.07359 -0.0279 1.0000 0.0506
-8.500 -0.5841 0.07533 0.06853 -0.0314 1.0000 0.0496
-8.250 -0.5924 0.07036 0.06348 -0.0342 1.0000 0.0488
-8.000 -0.5981 0.06551 0.05850 -0.0363 1.0000 0.0481
-7.750 -0.6004 0.06076 0.05351 -0.0378 1.0000 0.0475
-7.500 -0.5986 0.05613 0.04856 -0.0386 1.0000 0.0468
-7.250 -0.5923 0.05181 0.04386 -0.0389 1.0000 0.0464
-7.000 -0.5822 0.04782 0.03945 -0.0389 1.0000 0.0463
-6.750 -0.5688 0.04421 0.03541 -0.0385 1.0000 0.0465
-6.500 -0.5527 0.04102 0.03182 -0.0380 1.0000 0.0473
-6.250 -0.5349 0.03842 0.02886 -0.0374 1.0000 0.0502
-6.000 -0.5153 0.03585 0.02580 -0.0366 1.0000 0.0530
-5.750 -0.4939 0.03335 0.02276 -0.0357 1.0000 0.0545
-5.500 -0.4713 0.03117 0.02016 -0.0345 1.0000 0.0558
-5.250 -0.4493 0.02905 0.01792 -0.0334 1.0000 0.0577
-5.000 -0.4282 0.02754 0.01636 -0.0323 1.0000 0.0623
-4.750 -0.4064 0.02630 0.01488 -0.0309 1.0000 0.0685
-4.500 -0.3864 0.02491 0.01350 -0.0293 1.0000 0.0730
-4.250 -0.3668 0.02378 0.01223 -0.0278 1.0000 0.0791
-4.000 -0.3479 0.02273 0.01115 -0.0265 1.0000 0.0909
-3.750 -0.3286 0.02162 0.01003 -0.0254 1.0000 0.1065
-3.500 -0.3094 0.02028 0.00888 -0.0246 1.0000 0.1403
-3.250 -0.2974 0.01764 0.00821 -0.0233 1.0000 0.4481
-3.000 -0.2864 0.01734 0.00843 -0.0190 1.0000 0.6147
-2.750 -0.2819 0.01751 0.00889 -0.0126 1.0000 0.7258
-2.500 -0.2829 0.01780 0.00938 -0.0044 1.0000 0.8051
-2.250 -0.2756 0.01789 0.00944 0.0013 1.0000 0.8576
-2.000 -0.2545 0.01777 0.00913 0.0028 1.0000 0.8870
-1.750 -0.2267 0.01764 0.00877 0.0024 1.0000 0.9124
-1.500 -0.1902 0.01754 0.00840 0.0001 0.9993 0.9368
-1.250 -0.1360 0.01756 0.00814 -0.0059 0.9924 0.9559
-1.000 -0.0795 0.01759 0.00794 -0.0125 0.9857 0.9746
-0.750 -0.0238 0.01758 0.00772 -0.0191 0.9779 0.9936
-0.500 0.0158 0.01764 0.00764 -0.0228 0.9666 1.0000
-0.250 0.0511 0.01773 0.00762 -0.0256 0.9544 1.0000
0.000 0.0864 0.01785 0.00763 -0.0282 0.9427 1.0000
0.250 0.1235 0.01799 0.00769 -0.0310 0.9320 1.0000
0.500 0.1640 0.01814 0.00781 -0.0342 0.9226 1.0000
0.750 0.1966 0.01831 0.00795 -0.0358 0.9107 1.0000
1.000 0.2290 0.01849 0.00813 -0.0373 0.8989 1.0000
1.250 0.2617 0.01869 0.00834 -0.0387 0.8876 1.0000
1.500 0.2948 0.01889 0.00860 -0.0401 0.8768 1.0000
1.750 0.3283 0.01908 0.00885 -0.0414 0.8661 1.0000
2.000 0.3567 0.01932 0.00917 -0.0418 0.8535 1.0000
2.250 0.3851 0.01958 0.00954 -0.0421 0.8410 1.0000
2.500 0.4136 0.01983 0.00991 -0.0424 0.8286 1.0000
2.750 0.4425 0.02008 0.01030 -0.0426 0.8160 1.0000
3.000 0.4712 0.02032 0.01070 -0.0427 0.8030 1.0000
3.250 0.4995 0.02054 0.01115 -0.0425 0.7890 1.0000
3.500 0.5270 0.02072 0.01154 -0.0421 0.7734 1.0000
3.750 0.5546 0.02081 0.01185 -0.0413 0.7557 1.0000
4.000 0.5809 0.02068 0.01193 -0.0397 0.7313 1.0000
4.250 0.6036 0.01996 0.01136 -0.0358 0.6847 1.0000
4.500 0.6199 0.01919 0.01036 -0.0305 0.5937 1.0000
4.750 0.6362 0.01933 0.01011 -0.0268 0.4673 1.0000
5.000 0.6438 0.02130 0.01059 -0.0235 0.2236 1.0000
5.250 0.6553 0.02390 0.01229 -0.0222 0.1221 1.0000
5.500 0.6728 0.02564 0.01385 -0.0211 0.0949 1.0000
5.750 0.6920 0.02720 0.01551 -0.0200 0.0832 1.0000
6.000 0.7123 0.02873 0.01703 -0.0190 0.0725 1.0000
6.250 0.7360 0.03019 0.01869 -0.0181 0.0651 1.0000
6.500 0.7616 0.03215 0.02058 -0.0175 0.0609 1.0000
6.750 0.7895 0.03394 0.02273 -0.0169 0.0561 1.0000
7.000 0.8145 0.03587 0.02490 -0.0165 0.0514 1.0000
7.250 0.8396 0.03851 0.02766 -0.0162 0.0492 1.0000
7.500 0.8630 0.04156 0.03107 -0.0156 0.0480 1.0000
7.750 0.8829 0.04474 0.03479 -0.0147 0.0472 1.0000
8.000 0.8989 0.04823 0.03882 -0.0136 0.0466 1.0000
8.250 0.9103 0.05184 0.04298 -0.0125 0.0455 1.0000
8.500 0.9171 0.05556 0.04721 -0.0113 0.0441 1.0000
8.750 0.9202 0.05937 0.05146 -0.0103 0.0428 1.0000
9.000 0.9191 0.06338 0.05584 -0.0094 0.0420 1.0000
9.250 0.9132 0.06762 0.06040 -0.0087 0.0418 1.0000
9.500 0.9020 0.07199 0.06503 -0.0083 0.0420 1.0000
9.750 0.8853 0.07625 0.06946 -0.0081 0.0423 1.0000
10.000 0.8661 0.08119 0.07453 -0.0096 0.0427 1.0000
10.250 0.8463 0.08708 0.08051 -0.0129 0.0432 1.0000
10.500 0.8283 0.09395 0.08743 -0.0176 0.0437 1.0000
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Polar data table (+)
Polar graphs
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