NACA 63A210 (naca63a210-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 63A210 (naca63a210-il) Reynolds number: 50,000 Max Cl/Cd: 31.28 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca63a210-il-50000-n5.txt Download as CSV file: xf-naca63a210-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63A210
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 -0.5806 0.09172 0.08522 -0.0203 1.0000 0.0520
-9.250 -0.5856 0.08558 0.07913 -0.0247 1.0000 0.0509
-9.000 -0.5956 0.07916 0.07274 -0.0300 1.0000 0.0499
-8.750 -0.6097 0.07370 0.06725 -0.0335 1.0000 0.0490
-8.500 -0.6209 0.06847 0.06189 -0.0359 1.0000 0.0482
-8.250 -0.6282 0.06360 0.05681 -0.0371 1.0000 0.0475
-8.000 -0.6315 0.05900 0.05193 -0.0376 1.0000 0.0470
-7.750 -0.6305 0.05474 0.04733 -0.0373 1.0000 0.0467
-7.500 -0.6255 0.05084 0.04306 -0.0366 1.0000 0.0466
-7.250 -0.6172 0.04729 0.03912 -0.0356 1.0000 0.0468
-7.000 -0.6059 0.04417 0.03564 -0.0345 1.0000 0.0476
-6.750 -0.5923 0.04161 0.03277 -0.0333 1.0000 0.0499
-6.500 -0.5773 0.03907 0.02982 -0.0321 1.0000 0.0525
-6.250 -0.5600 0.03651 0.02674 -0.0307 1.0000 0.0544
-6.000 -0.5404 0.03407 0.02386 -0.0294 1.0000 0.0555
-5.750 -0.5189 0.03195 0.02133 -0.0281 1.0000 0.0569
-5.500 -0.4968 0.02988 0.01905 -0.0269 1.0000 0.0588
-5.250 -0.4757 0.02827 0.01742 -0.0258 1.0000 0.0629
-5.000 -0.4540 0.02703 0.01600 -0.0245 1.0000 0.0696
-4.750 -0.4326 0.02567 0.01449 -0.0231 1.0000 0.0748
-4.500 -0.4126 0.02445 0.01323 -0.0216 1.0000 0.0817
-4.250 -0.3929 0.02334 0.01208 -0.0204 1.0000 0.0949
-4.000 -0.3727 0.02215 0.01089 -0.0193 1.0000 0.1131
-3.750 -0.3513 0.02056 0.00965 -0.0190 0.9987 0.1644
-3.500 -0.3324 0.01811 0.00906 -0.0184 0.9919 0.4750
-3.250 -0.3112 0.01786 0.00923 -0.0158 0.9844 0.6362
-3.000 -0.2922 0.01795 0.00950 -0.0120 0.9757 0.7345
-2.750 -0.2729 0.01806 0.00965 -0.0078 0.9684 0.8065
-2.500 -0.2447 0.01802 0.00948 -0.0063 0.9620 0.8470
-2.250 -0.2091 0.01791 0.00909 -0.0074 0.9566 0.8744
-2.000 -0.1705 0.01777 0.00874 -0.0094 0.9504 0.8960
-1.750 -0.1271 0.01764 0.00839 -0.0126 0.9451 0.9167
-1.500 -0.0812 0.01752 0.00803 -0.0166 0.9399 0.9366
-1.250 -0.0356 0.01738 0.00772 -0.0206 0.9330 0.9562
-1.000 0.0152 0.01723 0.00742 -0.0259 0.9269 0.9735
-0.750 0.0642 0.01706 0.00712 -0.0310 0.9186 0.9920
-0.500 0.1002 0.01690 0.00688 -0.0336 0.9062 1.0000
-0.250 0.1252 0.01680 0.00670 -0.0340 0.8905 1.0000
0.000 0.1504 0.01674 0.00657 -0.0343 0.8751 1.0000
0.250 0.1758 0.01672 0.00650 -0.0345 0.8601 1.0000
0.500 0.2008 0.01674 0.00647 -0.0345 0.8447 1.0000
0.750 0.2263 0.01680 0.00648 -0.0345 0.8294 1.0000
1.000 0.2526 0.01687 0.00653 -0.0345 0.8140 1.0000
1.250 0.2796 0.01695 0.00660 -0.0346 0.7979 1.0000
1.500 0.3071 0.01703 0.00666 -0.0346 0.7811 1.0000
1.750 0.3345 0.01713 0.00674 -0.0345 0.7649 1.0000
2.000 0.3616 0.01726 0.00688 -0.0344 0.7498 1.0000
2.250 0.3885 0.01742 0.00710 -0.0343 0.7367 1.0000
2.500 0.4155 0.01761 0.00733 -0.0342 0.7243 1.0000
2.750 0.4426 0.01780 0.00757 -0.0340 0.7117 1.0000
3.000 0.4687 0.01804 0.00789 -0.0337 0.6985 1.0000
3.250 0.4945 0.01830 0.00829 -0.0333 0.6843 1.0000
3.500 0.5203 0.01855 0.00863 -0.0327 0.6684 1.0000
3.750 0.5464 0.01878 0.00893 -0.0320 0.6515 1.0000
4.000 0.5734 0.01904 0.00921 -0.0313 0.6338 1.0000
4.250 0.5989 0.01942 0.00967 -0.0303 0.6094 1.0000
4.500 0.6177 0.01975 0.01015 -0.0284 0.5691 1.0000
4.750 0.6621 0.02367 0.01255 -0.0298 0.5109 1.0000
5.000 0.6597 0.02150 0.01193 -0.0252 0.4643 1.0000
5.250 0.6796 0.02190 0.01229 -0.0233 0.3904 1.0000
5.500 0.6903 0.02311 0.01257 -0.0206 0.2198 1.0000
5.750 0.7016 0.02535 0.01392 -0.0189 0.1295 1.0000
6.000 0.7173 0.02704 0.01546 -0.0173 0.1026 1.0000
6.250 0.7338 0.02858 0.01692 -0.0159 0.0859 1.0000
6.500 0.7517 0.03005 0.01851 -0.0144 0.0762 1.0000
6.750 0.7685 0.03175 0.02015 -0.0129 0.0693 1.0000
7.000 0.7900 0.03317 0.02184 -0.0117 0.0623 1.0000
7.250 0.8112 0.03486 0.02364 -0.0107 0.0575 1.0000
7.500 0.8353 0.03722 0.02600 -0.0101 0.0548 1.0000
7.750 0.8597 0.03956 0.02875 -0.0092 0.0530 1.0000
8.000 0.8810 0.04215 0.03179 -0.0082 0.0509 1.0000
8.250 0.8983 0.04474 0.03478 -0.0070 0.0481 1.0000
8.500 0.9132 0.04729 0.03764 -0.0059 0.0455 1.0000
8.750 0.9256 0.05023 0.04089 -0.0047 0.0441 1.0000
9.000 0.9347 0.05362 0.04469 -0.0033 0.0434 1.0000
9.250 0.9400 0.05725 0.04867 -0.0019 0.0429 1.0000
9.500 0.9412 0.06107 0.05283 -0.0005 0.0426 1.0000
9.750 0.9378 0.06503 0.05712 0.0008 0.0425 1.0000
10.000 0.9294 0.06908 0.06147 0.0019 0.0425 1.0000
10.250 0.9146 0.07309 0.06574 0.0030 0.0427 1.0000
10.500 0.8945 0.07763 0.07050 0.0028 0.0430 1.0000
10.750 0.8664 0.08385 0.07694 -0.0003 0.0436 1.0000
11.000 0.8314 0.09351 0.08668 -0.0082 0.0448 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 63A210 (naca63a210-il)