NACA 63A210 (naca63a210-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63A210 (naca63a210-il) Reynolds number: 100,000 Max Cl/Cd: 37.62 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca63a210-il-100000.txt Download as CSV file: xf-naca63a210-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5670 0.09530 0.09078 -0.0037 0.7256 0.0921
-8.500 -0.5800 0.08917 0.08470 -0.0134 0.7256 0.0947
-8.250 -0.6019 0.08414 0.07953 -0.0220 0.7258 0.0957
-8.000 -0.5816 0.07960 0.07514 -0.0182 0.7256 0.1003
-7.750 -0.5788 0.07565 0.07113 -0.0203 0.7256 0.1060
-7.500 -0.6004 0.07114 0.06614 -0.0277 0.7258 0.1113
-7.250 -0.5745 0.06698 0.06230 -0.0248 0.7257 0.1193
-7.000 -0.5709 0.06276 0.05794 -0.0266 0.7259 0.1300
-6.750 -0.5612 0.05945 0.05452 -0.0269 0.7260 0.1460
-5.250 -0.4379 0.03512 0.02698 -0.0287 0.7265 0.0810
-5.000 -0.4091 0.03098 0.02241 -0.0277 0.7267 0.0646
-4.750 -0.3807 0.02800 0.01887 -0.0267 0.7269 0.0568
-4.500 -0.3506 0.02707 0.01748 -0.0259 0.7272 0.0536
-4.250 -0.3222 0.02460 0.01486 -0.0255 0.7276 0.0530
-4.000 -0.2946 0.02239 0.01263 -0.0252 0.7279 0.0562
-3.750 -0.2681 0.02094 0.01119 -0.0248 0.7283 0.0616
-3.500 -0.2424 0.01971 0.00994 -0.0240 0.7287 0.0655
-3.250 -0.2191 0.01848 0.00870 -0.0231 0.7291 0.0732
-3.000 -0.1952 0.01732 0.00762 -0.0224 0.7295 0.1049
-2.750 -0.1992 0.01444 0.00779 -0.0148 0.7300 0.7341
-2.500 -0.1890 0.01497 0.00851 -0.0069 0.7304 0.8421
-2.250 -0.1531 0.01606 0.00942 -0.0026 0.7304 0.9118
-2.000 -0.1116 0.01602 0.00910 -0.0054 0.7307 0.9263
-1.750 -0.0677 0.01596 0.00880 -0.0090 0.7310 0.9399
-1.500 -0.0221 0.01588 0.00851 -0.0131 0.7313 0.9530
-1.250 0.0246 0.01580 0.00822 -0.0176 0.7316 0.9660
-1.000 0.0743 0.01567 0.00795 -0.0229 0.7319 0.9778
-0.750 0.1229 0.01553 0.00770 -0.0282 0.7322 0.9899
-0.500 0.1683 0.01539 0.00746 -0.0330 0.7325 1.0000
-0.250 0.1932 0.01533 0.00738 -0.0339 0.7328 1.0000
0.000 0.2179 0.01533 0.00736 -0.0348 0.7331 1.0000
0.250 0.2417 0.01539 0.00741 -0.0353 0.7328 1.0000
0.500 0.2651 0.01551 0.00753 -0.0357 0.7322 1.0000
0.750 0.2885 0.01567 0.00770 -0.0361 0.7316 1.0000
1.000 0.3116 0.01588 0.00794 -0.0364 0.7309 1.0000
1.250 0.3350 0.01616 0.00825 -0.0367 0.7305 1.0000
1.500 0.3582 0.01649 0.00862 -0.0369 0.7289 1.0000
1.750 0.3814 0.01686 0.00906 -0.0370 0.7265 1.0000
2.000 0.4051 0.01729 0.00953 -0.0372 0.7249 1.0000
2.250 0.4290 0.01775 0.01005 -0.0373 0.7230 1.0000
2.500 0.4529 0.01825 0.01061 -0.0373 0.7210 1.0000
2.750 0.4763 0.01876 0.01113 -0.0368 0.7175 1.0000
3.000 0.4987 0.01936 0.01191 -0.0369 0.7119 1.0000
3.250 0.5214 0.01976 0.01233 -0.0357 0.7041 1.0000
3.500 0.5429 0.02032 0.01301 -0.0350 0.6948 1.0000
3.750 0.5643 0.02074 0.01348 -0.0335 0.6830 1.0000
4.000 0.5854 0.02111 0.01395 -0.0316 0.6688 1.0000
4.250 0.6063 0.02148 0.01438 -0.0296 0.6529 1.0000
4.500 0.6272 0.02188 0.01482 -0.0274 0.6359 1.0000
4.750 0.6482 0.02241 0.01536 -0.0251 0.6184 1.0000
5.000 0.6679 0.02292 0.01604 -0.0234 0.5989 1.0000
5.250 0.6896 0.02323 0.01639 -0.0211 0.5788 1.0000
5.500 0.7112 0.02366 0.01688 -0.0187 0.5570 1.0000
5.750 0.7278 0.02543 0.01872 -0.0163 0.5299 1.0000
6.000 0.7405 0.02769 0.02112 -0.0137 0.4944 1.0000
6.250 0.7753 0.02061 0.01415 -0.0116 0.3172 1.0000
6.500 0.7836 0.02212 0.01449 -0.0091 0.1909 1.0000
6.750 0.7972 0.02340 0.01533 -0.0071 0.1435 1.0000
7.000 0.8111 0.02471 0.01645 -0.0050 0.1068 1.0000
7.250 0.8226 0.02657 0.01800 -0.0023 0.0845 1.0000
7.500 0.8387 0.02820 0.01966 -0.0005 0.0678 1.0000
7.750 0.8553 0.03061 0.02191 0.0014 0.0582 1.0000
8.000 0.8758 0.03197 0.02356 0.0027 0.0497 1.0000
8.250 0.8969 0.03578 0.02729 0.0039 0.0454 1.0000
8.500 0.9173 0.03858 0.03057 0.0054 0.0440 1.0000
8.750 0.9337 0.04202 0.03450 0.0070 0.0429 1.0000
9.000 0.9453 0.04540 0.03838 0.0085 0.0412 1.0000
9.250 0.9527 0.04891 0.04232 0.0099 0.0396 1.0000
9.500 0.9547 0.05302 0.04685 0.0113 0.0394 1.0000
9.750 0.9503 0.05771 0.05194 0.0124 0.0403 1.0000
10.000 0.9414 0.06235 0.05689 0.0131 0.0413 1.0000
10.250 0.9277 0.06668 0.06144 0.0135 0.0421 1.0000
10.500 0.9117 0.07130 0.06623 0.0125 0.0427 1.0000
10.750 0.8950 0.07666 0.07173 0.0095 0.0433 1.0000
11.000 0.8787 0.08264 0.07781 0.0058 0.0439 1.0000
11.250 0.8795 0.08759 0.08283 0.0049 0.0464 1.0000
11.500 0.8339 0.09742 0.09285 -0.0044 0.0477 1.0000
11.750 0.6793 0.10057 0.09620 0.0010 0.0552 1.0000
12.000 0.6723 0.10620 0.10181 -0.0002 0.0569 1.0000
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Polar data table (+)
Polar graphs
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