NACA 1408 (naca1408-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1408 (naca1408-il) Reynolds number: 100,000 Max Cl/Cd: 44.19 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1408-il-100000.txt Download as CSV file: xf-naca1408-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5966 0.10482 0.09980 0.0042 1.0000 0.1145
-9.000 -0.6051 0.10091 0.09595 -0.0003 1.0000 0.1197
-8.750 -0.6405 0.09570 0.09089 -0.0145 1.0000 0.1214
-8.500 -0.6004 0.09242 0.08754 -0.0024 1.0000 0.1260
-8.250 -0.6005 0.08866 0.08382 -0.0045 1.0000 0.1314
-8.000 -0.6317 0.08155 0.07671 -0.0196 1.0000 0.1362
-7.750 -0.6030 0.07979 0.07503 -0.0104 1.0000 0.1417
-7.500 -0.6227 0.07311 0.06817 -0.0227 1.0000 0.1504
-7.250 -0.5974 0.07123 0.06645 -0.0159 1.0000 0.1586
-7.000 -0.5950 0.06654 0.06171 -0.0187 1.0000 0.1682
-6.750 -0.5910 0.06221 0.05726 -0.0214 1.0000 0.1808
-6.500 -0.5903 0.04122 0.03407 -0.0301 1.0000 0.0796
-6.250 -0.5738 0.03652 0.02918 -0.0295 1.0000 0.0774
-6.000 -0.5555 0.03279 0.02497 -0.0284 1.0000 0.0765
-5.750 -0.5351 0.03024 0.02178 -0.0271 1.0000 0.0791
-5.500 -0.5133 0.02769 0.01870 -0.0258 1.0000 0.0804
-5.250 -0.4911 0.02498 0.01584 -0.0250 1.0000 0.0832
-5.000 -0.4678 0.02359 0.01429 -0.0241 1.0000 0.0894
-4.750 -0.4431 0.02214 0.01245 -0.0229 1.0000 0.0934
-4.500 -0.4194 0.02043 0.01082 -0.0222 1.0000 0.0997
-4.250 -0.3948 0.01940 0.00960 -0.0212 1.0000 0.1079
-4.000 -0.3712 0.01807 0.00841 -0.0203 1.0000 0.1166
-3.750 -0.3479 0.01703 0.00745 -0.0194 1.0000 0.1313
-3.500 -0.3252 0.01590 0.00653 -0.0183 1.0000 0.1582
-3.250 -0.3044 0.01415 0.00558 -0.0173 1.0000 0.2691
-3.000 -0.2854 0.01274 0.00524 -0.0158 1.0000 0.4750
-2.750 -0.2669 0.01192 0.00515 -0.0132 1.0000 0.6514
-2.500 -0.2492 0.01150 0.00529 -0.0091 1.0000 0.8193
-2.250 -0.1737 0.01167 0.00536 -0.0160 1.0000 0.9740
-2.000 -0.1124 0.01157 0.00493 -0.0232 1.0000 1.0000
-1.750 -0.1019 0.01143 0.00467 -0.0206 1.0000 1.0000
-1.500 -0.0893 0.01137 0.00448 -0.0183 1.0000 1.0000
-1.250 -0.0746 0.01137 0.00435 -0.0163 1.0000 1.0000
-1.000 -0.0578 0.01140 0.00427 -0.0146 1.0000 1.0000
-0.750 -0.0395 0.01148 0.00425 -0.0133 1.0000 1.0000
-0.500 -0.0203 0.01159 0.00428 -0.0121 1.0000 1.0000
-0.250 -0.0005 0.01173 0.00435 -0.0112 1.0000 1.0000
0.000 0.0198 0.01192 0.00448 -0.0104 1.0000 1.0000
0.250 0.0402 0.01215 0.00467 -0.0097 1.0000 1.0000
0.500 0.0607 0.01243 0.00493 -0.0092 1.0000 1.0000
0.750 0.0810 0.01277 0.00526 -0.0088 1.0000 1.0000
1.000 0.1140 0.01317 0.00567 -0.0110 0.9956 1.0000
1.250 0.1723 0.01351 0.00606 -0.0177 0.9814 1.0000
1.500 0.2284 0.01370 0.00634 -0.0238 0.9645 1.0000
1.750 0.2853 0.01375 0.00651 -0.0296 0.9470 1.0000
2.000 0.3427 0.01363 0.00656 -0.0352 0.9295 1.0000
2.250 0.3899 0.01343 0.00650 -0.0383 0.9075 1.0000
2.500 0.4320 0.01313 0.00633 -0.0398 0.8833 1.0000
2.750 0.4626 0.01293 0.00623 -0.0389 0.8531 1.0000
3.000 0.4881 0.01280 0.00614 -0.0370 0.8179 1.0000
3.250 0.5118 0.01270 0.00603 -0.0346 0.7786 1.0000
3.500 0.5331 0.01268 0.00592 -0.0318 0.7279 1.0000
3.750 0.5535 0.01279 0.00585 -0.0289 0.6664 1.0000
4.000 0.5745 0.01306 0.00593 -0.0267 0.6037 1.0000
4.250 0.5953 0.01347 0.00610 -0.0246 0.5332 1.0000
4.500 0.6148 0.01406 0.00636 -0.0225 0.4361 1.0000
4.750 0.6251 0.01622 0.00711 -0.0197 0.1998 1.0000
5.000 0.6420 0.01820 0.00845 -0.0179 0.1328 1.0000
5.250 0.6631 0.01955 0.00966 -0.0167 0.1145 1.0000
5.500 0.6858 0.02096 0.01093 -0.0156 0.1041 1.0000
5.750 0.7104 0.02220 0.01224 -0.0148 0.0948 1.0000
6.000 0.7353 0.02410 0.01406 -0.0141 0.0887 1.0000
6.250 0.7610 0.02557 0.01578 -0.0133 0.0830 1.0000
6.500 0.7855 0.02768 0.01784 -0.0129 0.0772 1.0000
6.750 0.8099 0.03012 0.02067 -0.0118 0.0749 1.0000
7.000 0.8322 0.03222 0.02329 -0.0106 0.0712 1.0000
7.250 0.8532 0.03475 0.02621 -0.0094 0.0685 1.0000
7.500 0.8712 0.03831 0.03032 -0.0078 0.0686 1.0000
7.750 0.8850 0.04257 0.03520 -0.0061 0.0698 1.0000
8.000 0.8956 0.04684 0.03999 -0.0045 0.0701 1.0000
8.250 0.9014 0.05188 0.04552 -0.0031 0.0719 1.0000
8.500 0.9169 0.05728 0.05100 -0.0024 0.0775 1.0000
9.250 0.8358 0.09320 0.08854 -0.0131 0.1582 1.0000
9.500 0.7911 0.10153 0.09677 -0.0248 0.1572 1.0000
9.750 0.7714 0.10709 0.10225 -0.0307 0.1501 1.0000
10.000 0.7899 0.11037 0.10557 -0.0269 0.1437 1.0000
10.250 0.7650 0.11622 0.11131 -0.0343 0.1381 1.0000
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Polar data table (+)
Polar graphs
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