NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66-209 (naca66209-il) Reynolds number: 500,000 Max Cl/Cd: 60.65 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca66209-il-500000-n5.txt Download as CSV file: xf-naca66209-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66-209
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5360 0.08358 0.08133 -0.0360 1.0000 0.0060
-9.500 -0.5429 0.07815 0.07594 -0.0396 1.0000 0.0056
-9.250 -0.5570 0.07141 0.06922 -0.0458 1.0000 0.0056
-9.000 -0.5747 0.06676 0.06456 -0.0478 1.0000 0.0056
-8.750 -0.5943 0.06255 0.06030 -0.0471 0.9987 0.0054
-8.500 -0.5902 0.05547 0.05302 -0.0521 0.9831 0.0056
-8.250 -0.5838 0.04811 0.04537 -0.0555 0.9716 0.0060
-8.000 -0.5761 0.04109 0.03797 -0.0569 0.9611 0.0060
-7.750 -0.5760 0.03159 0.02779 -0.0553 0.9487 0.0067
-7.500 -0.5756 0.02257 0.01778 -0.0519 0.9378 0.0075
-7.250 -0.5545 0.02157 0.01661 -0.0513 0.9307 0.0078
-7.000 -0.5315 0.02079 0.01566 -0.0509 0.9252 0.0083
-6.750 -0.5099 0.01920 0.01381 -0.0501 0.9194 0.0088
-6.500 -0.4868 0.01789 0.01223 -0.0495 0.9141 0.0096
-6.250 -0.4633 0.01654 0.01063 -0.0488 0.9095 0.0103
-6.000 -0.4382 0.01602 0.00997 -0.0485 0.9043 0.0110
-5.750 -0.4153 0.01461 0.00838 -0.0478 0.8994 0.0121
-5.500 -0.3905 0.01405 0.00775 -0.0475 0.8951 0.0128
-5.250 -0.3656 0.01347 0.00709 -0.0472 0.8904 0.0135
-5.000 -0.3406 0.01292 0.00644 -0.0468 0.8863 0.0143
-4.750 -0.3153 0.01247 0.00592 -0.0465 0.8827 0.0155
-4.500 -0.2900 0.01201 0.00540 -0.0461 0.8784 0.0165
-4.250 -0.2649 0.01154 0.00485 -0.0458 0.8741 0.0171
-4.000 -0.2400 0.01107 0.00430 -0.0454 0.8704 0.0178
-3.750 -0.2159 0.01043 0.00357 -0.0449 0.8664 0.0194
-3.500 -0.1900 0.01010 0.00322 -0.0447 0.8624 0.0211
-3.250 -0.1636 0.00987 0.00296 -0.0445 0.8590 0.0238
-3.000 -0.1370 0.00966 0.00270 -0.0444 0.8559 0.0262
-2.750 -0.1103 0.00946 0.00246 -0.0444 0.8527 0.0282
-2.500 -0.0837 0.00920 0.00217 -0.0443 0.8490 0.0341
-2.250 -0.0567 0.00904 0.00199 -0.0442 0.8456 0.0395
-2.000 -0.0303 0.00878 0.00183 -0.0442 0.8425 0.0705
-1.750 -0.0076 0.00785 0.00160 -0.0439 0.8393 0.2791
-1.500 0.0087 0.00625 0.00143 -0.0427 0.8355 0.6728
-1.250 0.0338 0.00613 0.00153 -0.0420 0.8324 0.7485
-1.000 0.0603 0.00613 0.00158 -0.0416 0.8296 0.7780
-0.500 0.1152 0.00616 0.00162 -0.0414 0.8238 0.8023
-0.250 0.1426 0.00619 0.00166 -0.0414 0.8208 0.8139
0.000 0.1698 0.00622 0.00171 -0.0412 0.8180 0.8241
0.250 0.1979 0.00624 0.00172 -0.0413 0.8152 0.8283
0.500 0.2258 0.00624 0.00173 -0.0414 0.8114 0.8311
0.750 0.2531 0.00623 0.00172 -0.0413 0.8026 0.8344
1.000 0.2801 0.00622 0.00168 -0.0411 0.7898 0.8377
1.250 0.3073 0.00622 0.00166 -0.0410 0.7761 0.8410
1.500 0.3340 0.00623 0.00167 -0.0407 0.7618 0.8436
1.750 0.3600 0.00625 0.00166 -0.0402 0.7378 0.8469
2.000 0.3851 0.00635 0.00164 -0.0396 0.6978 0.8507
2.250 0.4017 0.00703 0.00170 -0.0374 0.5429 0.8551
2.500 0.4119 0.00853 0.00218 -0.0346 0.2982 0.8592
2.750 0.4281 0.00969 0.00259 -0.0331 0.1123 0.8637
3.000 0.4506 0.01027 0.00288 -0.0324 0.0422 0.8680
3.250 0.4757 0.01050 0.00311 -0.0320 0.0337 0.8717
3.500 0.5010 0.01071 0.00338 -0.0316 0.0298 0.8759
3.750 0.5258 0.01101 0.00369 -0.0312 0.0253 0.8806
4.000 0.5500 0.01135 0.00409 -0.0306 0.0224 0.8848
4.250 0.5743 0.01163 0.00443 -0.0300 0.0207 0.8892
4.500 0.5987 0.01194 0.00480 -0.0295 0.0187 0.8941
4.750 0.6225 0.01227 0.00517 -0.0289 0.0172 0.8989
5.000 0.6451 0.01268 0.00564 -0.0280 0.0162 0.9044
5.250 0.6668 0.01329 0.00631 -0.0270 0.0152 0.9106
5.500 0.6852 0.01419 0.00732 -0.0254 0.0144 0.9168
5.750 0.7076 0.01471 0.00792 -0.0245 0.0141 0.9234
6.000 0.7289 0.01534 0.00866 -0.0234 0.0137 0.9299
6.250 0.7508 0.01597 0.00939 -0.0224 0.0131 0.9374
6.500 0.7729 0.01653 0.01005 -0.0215 0.0123 0.9452
6.750 0.7955 0.01730 0.01092 -0.0207 0.0117 0.9546
7.000 0.8204 0.01811 0.01184 -0.0205 0.0111 0.9649
7.500 0.8766 0.01958 0.01350 -0.0218 0.0099 1.0000
7.750 0.8976 0.02157 0.01571 -0.0211 0.0091 1.0000
8.000 0.9208 0.02244 0.01675 -0.0207 0.0087 1.0000
8.250 0.9421 0.02407 0.01863 -0.0199 0.0082 1.0000
8.500 0.9616 0.02600 0.02084 -0.0190 0.0075 1.0000
8.750 0.9779 0.02847 0.02364 -0.0175 0.0071 1.0000
9.000 0.9930 0.03058 0.02603 -0.0161 0.0066 1.0000
9.250 1.0077 0.03227 0.02796 -0.0148 0.0063 1.0000
9.500 1.0256 0.03273 0.02850 -0.0140 0.0061 1.0000
9.750 1.0437 0.03288 0.02868 -0.0132 0.0059 1.0000
10.000 1.0325 0.03911 0.03554 -0.0090 0.0055 1.0000
10.250 0.9652 0.05400 0.05124 0.0001 0.0051 1.0000
10.500 0.9403 0.05860 0.05604 0.0038 0.0051 1.0000
10.750 0.9115 0.06405 0.06166 0.0058 0.0051 1.0000
11.000 0.8881 0.06914 0.06689 0.0057 0.0052 1.0000
11.250 0.8657 0.07504 0.07290 0.0036 0.0053 1.0000
11.500 0.8452 0.08223 0.08018 -0.0011 0.0054 1.0000
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Polar data table (+)
Polar graphs
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