NACA 1408 (naca1408-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1408 (naca1408-il) Reynolds number: 500,000 Max Cl/Cd: 66.64 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1408-il-500000.txt Download as CSV file: xf-naca1408-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1408
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.8112 0.04158 0.03856 -0.0342 1.0000 0.0140
-9.250 -0.8175 0.03542 0.03188 -0.0338 1.0000 0.0140
-9.000 -0.8109 0.03152 0.02761 -0.0331 1.0000 0.0143
-8.750 -0.7946 0.02964 0.02554 -0.0324 1.0000 0.0147
-8.500 -0.7748 0.02857 0.02434 -0.0319 1.0000 0.0153
-8.250 -0.7550 0.02731 0.02292 -0.0313 1.0000 0.0161
-8.000 -0.7376 0.02501 0.02029 -0.0302 1.0000 0.0170
-7.750 -0.7191 0.02284 0.01775 -0.0290 1.0000 0.0177
-7.500 -0.6978 0.02159 0.01623 -0.0280 1.0000 0.0182
-7.250 -0.6810 0.01859 0.01291 -0.0266 1.0000 0.0192
-7.000 -0.6587 0.01781 0.01208 -0.0258 1.0000 0.0202
-6.750 -0.6357 0.01725 0.01144 -0.0250 1.0000 0.0214
-6.500 -0.6124 0.01671 0.01081 -0.0242 1.0000 0.0230
-6.250 -0.5887 0.01631 0.01030 -0.0233 1.0000 0.0242
-6.000 -0.5685 0.01445 0.00829 -0.0221 1.0000 0.0260
-5.750 -0.5458 0.01384 0.00766 -0.0212 1.0000 0.0278
-5.500 -0.5225 0.01342 0.00720 -0.0203 1.0000 0.0300
-5.250 -0.4989 0.01312 0.00684 -0.0195 1.0000 0.0320
-5.000 -0.4771 0.01209 0.00572 -0.0184 1.0000 0.0344
-4.750 -0.4542 0.01152 0.00513 -0.0175 1.0000 0.0371
-4.500 -0.4306 0.01119 0.00478 -0.0167 1.0000 0.0400
-4.250 -0.4068 0.01090 0.00445 -0.0160 1.0000 0.0422
-4.000 -0.3832 0.01035 0.00385 -0.0152 1.0000 0.0453
-3.750 -0.3590 0.01001 0.00351 -0.0146 1.0000 0.0495
-3.500 -0.3345 0.00978 0.00326 -0.0140 1.0000 0.0531
-3.250 -0.3038 0.00943 0.00293 -0.0148 0.9988 0.0612
-3.000 -0.2666 0.00892 0.00261 -0.0169 0.9961 0.1000
-2.750 -0.2300 0.00834 0.00240 -0.0192 0.9936 0.1870
-2.500 -0.1945 0.00787 0.00226 -0.0212 0.9896 0.2690
-2.250 -0.1578 0.00741 0.00213 -0.0234 0.9862 0.3588
-2.000 -0.1200 0.00695 0.00203 -0.0258 0.9834 0.4569
-1.750 -0.0870 0.00646 0.00195 -0.0271 0.9778 0.5666
-1.500 -0.0521 0.00603 0.00188 -0.0286 0.9732 0.6680
-1.250 -0.0206 0.00564 0.00185 -0.0291 0.9672 0.7661
-1.000 0.0066 0.00533 0.00187 -0.0283 0.9587 0.8600
-0.750 0.0343 0.00522 0.00187 -0.0276 0.9486 0.9114
-0.500 0.0674 0.00519 0.00186 -0.0281 0.9390 0.9513
-0.250 0.1048 0.00517 0.00183 -0.0296 0.9273 0.9732
0.000 0.1433 0.00517 0.00178 -0.0316 0.9128 0.9862
0.250 0.1842 0.00517 0.00173 -0.0342 0.8959 0.9956
0.500 0.2182 0.00517 0.00166 -0.0354 0.8740 1.0000
0.750 0.2430 0.00520 0.00159 -0.0345 0.8478 1.0000
1.000 0.2679 0.00526 0.00154 -0.0337 0.8179 1.0000
1.250 0.2929 0.00535 0.00151 -0.0329 0.7864 1.0000
1.500 0.3177 0.00549 0.00150 -0.0321 0.7506 1.0000
1.750 0.3414 0.00572 0.00149 -0.0310 0.6942 1.0000
2.000 0.3654 0.00597 0.00151 -0.0301 0.6399 1.0000
2.250 0.3901 0.00619 0.00157 -0.0294 0.5979 1.0000
2.500 0.4147 0.00643 0.00165 -0.0287 0.5556 1.0000
2.750 0.4393 0.00671 0.00175 -0.0280 0.5093 1.0000
3.000 0.4639 0.00700 0.00186 -0.0274 0.4626 1.0000
3.250 0.4885 0.00733 0.00200 -0.0268 0.4092 1.0000
3.500 0.5125 0.00778 0.00217 -0.0262 0.3416 1.0000
3.750 0.5362 0.00834 0.00241 -0.0256 0.2623 1.0000
4.000 0.5590 0.00908 0.00273 -0.0250 0.1698 1.0000
4.250 0.5811 0.01004 0.00320 -0.0242 0.0746 1.0000
4.500 0.6059 0.01055 0.00360 -0.0237 0.0551 1.0000
4.750 0.6313 0.01097 0.00404 -0.0232 0.0494 1.0000
5.000 0.6569 0.01134 0.00443 -0.0227 0.0454 1.0000
5.250 0.6810 0.01198 0.00508 -0.0221 0.0411 1.0000
5.500 0.7060 0.01246 0.00562 -0.0216 0.0390 1.0000
5.750 0.7313 0.01287 0.00609 -0.0211 0.0363 1.0000
6.000 0.7559 0.01340 0.00664 -0.0206 0.0338 1.0000
6.250 0.7759 0.01485 0.00815 -0.0194 0.0305 1.0000
6.500 0.8021 0.01507 0.00843 -0.0191 0.0289 1.0000
6.750 0.8269 0.01559 0.00902 -0.0185 0.0268 1.0000
7.000 0.8510 0.01621 0.00967 -0.0180 0.0250 1.0000
7.250 0.8694 0.01838 0.01191 -0.0167 0.0227 1.0000
7.500 0.8952 0.01857 0.01220 -0.0163 0.0217 1.0000
7.750 0.9195 0.01912 0.01284 -0.0158 0.0202 1.0000
8.000 0.9431 0.01984 0.01365 -0.0152 0.0190 1.0000
8.250 0.9661 0.02058 0.01444 -0.0146 0.0180 1.0000
8.500 0.9826 0.02349 0.01753 -0.0133 0.0169 1.0000
8.750 1.0047 0.02443 0.01867 -0.0124 0.0164 1.0000
9.000 1.0254 0.02570 0.02016 -0.0115 0.0156 1.0000
9.250 1.0454 0.02691 0.02156 -0.0105 0.0147 1.0000
9.500 1.0653 0.02789 0.02266 -0.0097 0.0140 1.0000
9.750 1.0837 0.02905 0.02396 -0.0088 0.0135 1.0000
10.000 1.1001 0.03048 0.02551 -0.0078 0.0131 1.0000
10.250 1.1065 0.03383 0.02917 -0.0059 0.0127 1.0000
10.500 1.0957 0.03960 0.03548 -0.0029 0.0125 1.0000
10.750 1.0940 0.04273 0.03897 -0.0007 0.0124 1.0000
11.000 1.0818 0.04644 0.04299 0.0019 0.0123 1.0000
11.250 1.0619 0.05038 0.04719 0.0043 0.0123 1.0000
11.500 1.0399 0.05514 0.05218 0.0042 0.0123 1.0000
11.750 1.0167 0.06125 0.05849 0.0012 0.0124 1.0000
12.500 0.9628 0.08589 0.08359 -0.0184 0.0127 1.0000
14.250 0.6125 0.15101 0.14885 -0.0310 0.0226 1.0000
14.500 0.6109 0.15444 0.15228 -0.0325 0.0224 1.0000
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Polar data table (+)
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