NACA 1408 (naca1408-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: NACA 1408 (naca1408-il) Reynolds number: 200,000 Max Cl/Cd: 47.31 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca1408-il-200000-n5.txt Download as CSV file: xf-naca1408-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6907 0.07910 0.07571 -0.0094 1.0000 0.0140
-9.500 -0.7449 0.05639 0.05287 -0.0284 1.0000 0.0130
-9.250 -0.7649 0.04811 0.04420 -0.0322 1.0000 0.0129
-9.000 -0.7740 0.04139 0.03698 -0.0331 1.0000 0.0131
-8.750 -0.7739 0.03597 0.03098 -0.0327 1.0000 0.0134
-8.500 -0.7661 0.03192 0.02641 -0.0319 1.0000 0.0139
-8.250 -0.7503 0.02964 0.02385 -0.0311 1.0000 0.0144
-8.000 -0.7319 0.02783 0.02177 -0.0304 1.0000 0.0151
-7.750 -0.7127 0.02602 0.01967 -0.0295 1.0000 0.0160
-7.500 -0.6920 0.02453 0.01789 -0.0287 1.0000 0.0175
-7.250 -0.6706 0.02301 0.01604 -0.0278 1.0000 0.0191
-7.000 -0.6493 0.02138 0.01413 -0.0268 1.0000 0.0204
-6.750 -0.6280 0.02009 0.01274 -0.0260 1.0000 0.0220
-6.500 -0.6051 0.01941 0.01192 -0.0253 1.0000 0.0244
-6.250 -0.5819 0.01861 0.01096 -0.0245 1.0000 0.0275
-6.000 -0.5587 0.01781 0.00998 -0.0236 1.0000 0.0295
-5.750 -0.5370 0.01681 0.00897 -0.0227 1.0000 0.0330
-5.500 -0.5137 0.01624 0.00831 -0.0220 1.0000 0.0366
-5.250 -0.4901 0.01572 0.00765 -0.0211 1.0000 0.0394
-5.000 -0.4678 0.01490 0.00683 -0.0203 1.0000 0.0435
-4.750 -0.4444 0.01442 0.00630 -0.0196 1.0000 0.0471
-4.500 -0.4207 0.01401 0.00581 -0.0188 1.0000 0.0507
-4.250 -0.3974 0.01347 0.00523 -0.0180 1.0000 0.0540
-4.000 -0.3737 0.01305 0.00477 -0.0173 1.0000 0.0582
-3.750 -0.3497 0.01271 0.00438 -0.0166 1.0000 0.0636
-3.500 -0.3257 0.01232 0.00405 -0.0160 1.0000 0.0756
-3.250 -0.3016 0.01192 0.00375 -0.0155 1.0000 0.0979
-3.000 -0.2774 0.01154 0.00350 -0.0150 1.0000 0.1333
-2.750 -0.2426 0.01112 0.00328 -0.0169 0.9959 0.1858
-2.500 -0.2071 0.01072 0.00309 -0.0188 0.9906 0.2454
-2.250 -0.1708 0.01030 0.00294 -0.0210 0.9858 0.3180
-2.000 -0.1376 0.00975 0.00282 -0.0225 0.9791 0.4244
-1.750 -0.1048 0.00914 0.00277 -0.0237 0.9730 0.5583
-1.500 -0.0742 0.00866 0.00274 -0.0241 0.9655 0.6751
-1.250 -0.0460 0.00831 0.00277 -0.0236 0.9565 0.7754
-1.000 -0.0142 0.00815 0.00280 -0.0236 0.9486 0.8558
-0.750 0.0224 0.00810 0.00280 -0.0249 0.9392 0.9109
-0.500 0.0641 0.00807 0.00276 -0.0274 0.9299 0.9485
-0.250 0.1075 0.00803 0.00269 -0.0305 0.9193 0.9735
0.000 0.1508 0.00798 0.00261 -0.0337 0.9057 0.9908
0.250 0.1894 0.00793 0.00252 -0.0358 0.8875 1.0000
0.500 0.2171 0.00791 0.00243 -0.0355 0.8649 1.0000
0.750 0.2431 0.00791 0.00236 -0.0348 0.8392 1.0000
1.000 0.2685 0.00795 0.00232 -0.0340 0.8121 1.0000
1.250 0.2935 0.00802 0.00229 -0.0331 0.7833 1.0000
1.500 0.3182 0.00813 0.00228 -0.0322 0.7524 1.0000
1.750 0.3427 0.00827 0.00230 -0.0313 0.7182 1.0000
2.000 0.3671 0.00845 0.00234 -0.0303 0.6817 1.0000
2.250 0.3914 0.00866 0.00240 -0.0294 0.6445 1.0000
2.500 0.4148 0.00894 0.00249 -0.0283 0.5936 1.0000
2.750 0.4375 0.00934 0.00257 -0.0272 0.5277 1.0000
3.000 0.4602 0.00978 0.00270 -0.0262 0.4585 1.0000
3.250 0.4835 0.01022 0.00289 -0.0254 0.3945 1.0000
3.500 0.5068 0.01072 0.00310 -0.0247 0.3268 1.0000
3.750 0.5306 0.01123 0.00337 -0.0241 0.2658 1.0000
4.000 0.5541 0.01182 0.00369 -0.0235 0.2034 1.0000
4.250 0.5775 0.01247 0.00410 -0.0229 0.1445 1.0000
4.500 0.6010 0.01314 0.00454 -0.0224 0.0974 1.0000
4.750 0.6249 0.01376 0.00505 -0.0218 0.0717 1.0000
5.000 0.6494 0.01430 0.00557 -0.0213 0.0603 1.0000
5.250 0.6741 0.01480 0.00613 -0.0207 0.0540 1.0000
5.500 0.6985 0.01534 0.00672 -0.0202 0.0499 1.0000
5.750 0.7216 0.01609 0.00750 -0.0195 0.0461 1.0000
6.000 0.7460 0.01662 0.00813 -0.0189 0.0431 1.0000
6.250 0.7699 0.01722 0.00884 -0.0183 0.0397 1.0000
6.500 0.7925 0.01804 0.00967 -0.0176 0.0358 1.0000
6.750 0.8153 0.01888 0.01063 -0.0169 0.0330 1.0000
7.000 0.8389 0.01956 0.01143 -0.0162 0.0295 1.0000
7.250 0.8613 0.02040 0.01231 -0.0156 0.0265 1.0000
7.500 0.8821 0.02171 0.01373 -0.0146 0.0243 1.0000
7.750 0.9052 0.02256 0.01481 -0.0139 0.0217 1.0000
8.000 0.9273 0.02351 0.01589 -0.0131 0.0194 1.0000
8.250 0.9486 0.02455 0.01704 -0.0124 0.0179 1.0000
8.500 0.9664 0.02646 0.01908 -0.0113 0.0166 1.0000
8.750 0.9867 0.02788 0.02077 -0.0103 0.0156 1.0000
9.000 1.0057 0.02943 0.02261 -0.0092 0.0143 1.0000
9.250 1.0227 0.03123 0.02468 -0.0081 0.0134 1.0000
9.500 1.0379 0.03317 0.02689 -0.0068 0.0127 1.0000
9.750 1.0514 0.03513 0.02910 -0.0055 0.0122 1.0000
10.000 1.0624 0.03724 0.03150 -0.0042 0.0118 1.0000
10.250 1.0687 0.03984 0.03438 -0.0025 0.0115 1.0000
10.500 1.0670 0.04328 0.03816 -0.0006 0.0112 1.0000
11.000 1.0400 0.05104 0.04657 0.0038 0.0109 1.0000
11.250 1.0225 0.05542 0.05122 0.0040 0.0108 1.0000
11.500 1.0029 0.06093 0.05698 0.0017 0.0109 1.0000
11.750 0.9819 0.06801 0.06426 -0.0032 0.0109 1.0000
12.000 0.8597 0.10862 0.10527 -0.0302 0.0127 1.0000
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Polar data table (+)
Polar graphs
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