NACA 66-206 (naca66206-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66-206 (naca66206-il) Reynolds number: 500,000 Max Cl/Cd: 71.69 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca66206-il-500000.txt Download as CSV file: xf-naca66206-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-206
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5189 0.08578 0.08350 -0.0200 1.0000 0.0102
-8.000 -0.5182 0.08224 0.08000 -0.0230 1.0000 0.0105
-7.750 -0.5225 0.07841 0.07620 -0.0260 1.0000 0.0105
-7.500 -0.5190 0.07432 0.07210 -0.0295 1.0000 0.0106
-7.250 -0.5121 0.07053 0.06827 -0.0320 1.0000 0.0108
-7.000 -0.5058 0.06673 0.06442 -0.0335 1.0000 0.0109
-6.750 -0.4991 0.06293 0.06056 -0.0343 1.0000 0.0109
-6.500 -0.4924 0.05934 0.05688 -0.0344 1.0000 0.0110
-6.250 -0.4867 0.05591 0.05336 -0.0336 1.0000 0.0110
-6.000 -0.4830 0.05274 0.05009 -0.0318 1.0000 0.0110
-5.750 -0.4797 0.04976 0.04700 -0.0295 1.0000 0.0111
-5.500 -0.4692 0.04633 0.04341 -0.0285 0.9994 0.0111
-5.250 -0.4394 0.04133 0.03813 -0.0313 0.9967 0.0111
-5.000 -0.4185 0.03219 0.02857 -0.0352 0.9934 0.0128
-4.750 -0.3911 0.02986 0.02607 -0.0370 0.9904 0.0145
-4.500 -0.3571 0.02854 0.02451 -0.0380 0.9877 0.0197
-4.250 -0.3208 0.02780 0.02344 -0.0389 0.9854 0.0209
-3.500 -0.2275 0.01675 0.01131 -0.0422 0.9786 0.0184
-3.250 -0.1963 0.01354 0.00769 -0.0419 0.9761 0.0148
-3.000 -0.1636 0.01222 0.00623 -0.0427 0.9739 0.0173
-2.750 -0.1288 0.01193 0.00587 -0.0442 0.9721 0.0206
-2.500 -0.0946 0.01096 0.00482 -0.0455 0.9707 0.0211
-2.250 -0.0625 0.00934 0.00309 -0.0467 0.9690 0.0256
-2.000 -0.0330 0.00894 0.00265 -0.0472 0.9650 0.0295
-1.750 -0.0026 0.00853 0.00218 -0.0479 0.9611 0.0404
-1.500 0.0197 0.00600 0.00181 -0.0483 0.9573 0.6718
-1.250 0.0434 0.00569 0.00197 -0.0470 0.9535 0.8248
-1.000 0.0629 0.00570 0.00213 -0.0445 0.9477 0.8815
-0.750 0.0858 0.00575 0.00219 -0.0428 0.9435 0.9086
-0.500 0.1055 0.00580 0.00225 -0.0405 0.9382 0.9299
-0.250 0.1255 0.00580 0.00225 -0.0382 0.9329 0.9460
0.000 0.1519 0.00577 0.00220 -0.0377 0.9289 0.9558
0.250 0.1797 0.00573 0.00216 -0.0376 0.9225 0.9615
0.500 0.2088 0.00567 0.00210 -0.0378 0.9167 0.9673
0.750 0.2389 0.00557 0.00198 -0.0381 0.9060 0.9718
1.000 0.2696 0.00546 0.00186 -0.0384 0.8926 0.9761
1.250 0.3004 0.00540 0.00180 -0.0389 0.8805 0.9813
1.500 0.3333 0.00530 0.00167 -0.0397 0.8574 0.9845
1.750 0.3646 0.00527 0.00150 -0.0401 0.8089 0.9881
2.000 0.3936 0.00549 0.00144 -0.0401 0.7121 0.9931
2.250 0.4025 0.00827 0.00190 -0.0379 0.1444 1.0000
2.500 0.4164 0.00914 0.00235 -0.0355 0.0357 1.0000
2.750 0.4354 0.00991 0.00321 -0.0338 0.0253 1.0000
3.000 0.4590 0.01040 0.00373 -0.0330 0.0236 1.0000
3.250 0.4825 0.01110 0.00451 -0.0323 0.0225 1.0000
3.500 0.5072 0.01169 0.00517 -0.0318 0.0201 1.0000
3.750 0.5316 0.01253 0.00607 -0.0311 0.0184 1.0000
4.000 0.5558 0.01373 0.00732 -0.0304 0.0162 1.0000
4.250 0.5813 0.01551 0.00923 -0.0296 0.0162 1.0000
4.500 0.6060 0.01775 0.01170 -0.0290 0.0133 1.0000
4.750 0.6322 0.01938 0.01357 -0.0282 0.0122 1.0000
5.000 0.6567 0.02260 0.01720 -0.0267 0.0120 1.0000
5.500 0.6876 0.03437 0.02984 -0.0229 0.0142 1.0000
5.750 0.7049 0.03783 0.03361 -0.0215 0.0142 1.0000
6.000 0.7208 0.04142 0.03750 -0.0201 0.0142 1.0000
6.500 0.7480 0.04889 0.04555 -0.0174 0.0141 1.0000
6.750 0.7596 0.05268 0.04957 -0.0162 0.0141 1.0000
7.000 0.7701 0.05643 0.05354 -0.0151 0.0140 1.0000
7.250 0.7803 0.05998 0.05728 -0.0143 0.0138 1.0000
7.500 0.7971 0.06264 0.06013 -0.0135 0.0129 1.0000
7.750 0.8044 0.06684 0.06448 -0.0133 0.0121 1.0000
8.000 0.8046 0.07129 0.06906 -0.0135 0.0119 1.0000
8.250 0.8009 0.07583 0.07370 -0.0142 0.0117 1.0000
8.500 0.7903 0.08002 0.07794 -0.0145 0.0117 1.0000
8.750 0.7773 0.08466 0.08262 -0.0167 0.0116 1.0000
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Polar data table (+)
Polar graphs
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