NACA 1408 (naca1408-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1408 (naca1408-il) Reynolds number: 200,000 Max Cl/Cd: 54.89 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1408-il-200000.txt Download as CSV file: xf-naca1408-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6229 0.10337 0.09982 -0.0032 1.0000 0.0538
-9.500 -0.6297 0.09724 0.09373 -0.0102 1.0000 0.0542
-9.250 -0.6382 0.08993 0.08645 -0.0191 1.0000 0.0543
-9.000 -0.6343 0.08641 0.08298 -0.0124 1.0000 0.0557
-8.750 -0.6245 0.08455 0.08112 -0.0099 1.0000 0.0572
-8.500 -0.6236 0.08060 0.07719 -0.0122 1.0000 0.0585
-8.250 -0.6261 0.07518 0.07177 -0.0176 1.0000 0.0598
-8.000 -0.6270 0.06908 0.06561 -0.0231 1.0000 0.0619
-7.000 -0.6306 0.03607 0.03035 -0.0306 1.0000 0.0434
-6.750 -0.6134 0.03231 0.02632 -0.0295 1.0000 0.0417
-6.500 -0.5971 0.02860 0.02213 -0.0281 1.0000 0.0415
-6.250 -0.5773 0.02627 0.01932 -0.0267 1.0000 0.0423
-6.000 -0.5589 0.02298 0.01568 -0.0256 1.0000 0.0447
-5.750 -0.5369 0.02141 0.01396 -0.0247 1.0000 0.0470
-5.500 -0.5138 0.01995 0.01232 -0.0237 1.0000 0.0492
-5.250 -0.4903 0.01893 0.01109 -0.0226 1.0000 0.0527
-5.000 -0.4670 0.01747 0.00944 -0.0216 1.0000 0.0558
-4.750 -0.4439 0.01633 0.00832 -0.0208 1.0000 0.0593
-4.500 -0.4203 0.01569 0.00762 -0.0199 1.0000 0.0643
-4.250 -0.3970 0.01479 0.00666 -0.0189 1.0000 0.0683
-4.000 -0.3740 0.01400 0.00594 -0.0181 1.0000 0.0740
-3.750 -0.3504 0.01344 0.00533 -0.0172 1.0000 0.0811
-3.500 -0.3270 0.01277 0.00471 -0.0164 1.0000 0.0917
-3.250 -0.3032 0.01198 0.00409 -0.0158 1.0000 0.1214
-3.000 -0.2799 0.01083 0.00368 -0.0156 1.0000 0.2542
-2.750 -0.2560 0.01017 0.00348 -0.0152 1.0000 0.3700
-2.500 -0.2322 0.00958 0.00337 -0.0147 1.0000 0.4882
-2.250 -0.2091 0.00903 0.00335 -0.0138 1.0000 0.6167
-2.000 -0.1880 0.00856 0.00343 -0.0119 1.0000 0.7538
-1.750 -0.1682 0.00838 0.00362 -0.0089 1.0000 0.8860
-1.500 -0.1088 0.00843 0.00365 -0.0147 1.0000 0.9894
-1.250 -0.0820 0.00845 0.00356 -0.0150 1.0000 1.0000
-1.000 -0.0648 0.00852 0.00355 -0.0135 1.0000 1.0000
-0.750 -0.0454 0.00864 0.00359 -0.0124 1.0000 1.0000
-0.500 -0.0114 0.00876 0.00365 -0.0142 0.9965 1.0000
-0.250 0.0358 0.00884 0.00366 -0.0185 0.9888 1.0000
0.000 0.0840 0.00889 0.00368 -0.0229 0.9813 1.0000
0.250 0.1316 0.00888 0.00366 -0.0272 0.9724 1.0000
0.500 0.1792 0.00882 0.00361 -0.0312 0.9625 1.0000
0.750 0.2253 0.00871 0.00353 -0.0349 0.9515 1.0000
1.000 0.2658 0.00859 0.00343 -0.0371 0.9367 1.0000
1.250 0.3004 0.00847 0.00334 -0.0381 0.9180 1.0000
1.500 0.3311 0.00836 0.00323 -0.0380 0.8967 1.0000
1.750 0.3569 0.00830 0.00316 -0.0369 0.8699 1.0000
2.000 0.3813 0.00829 0.00310 -0.0355 0.8404 1.0000
2.250 0.4050 0.00834 0.00308 -0.0340 0.8072 1.0000
2.500 0.4280 0.00844 0.00305 -0.0323 0.7659 1.0000
2.750 0.4508 0.00861 0.00307 -0.0307 0.7180 1.0000
3.000 0.4735 0.00886 0.00310 -0.0291 0.6653 1.0000
3.250 0.4962 0.00918 0.00319 -0.0277 0.6075 1.0000
3.500 0.5195 0.00952 0.00333 -0.0266 0.5542 1.0000
3.750 0.5429 0.00989 0.00354 -0.0256 0.5007 1.0000
4.000 0.5658 0.01034 0.00376 -0.0246 0.4356 1.0000
4.250 0.5872 0.01103 0.00404 -0.0235 0.3381 1.0000
4.500 0.6037 0.01265 0.00465 -0.0221 0.1496 1.0000
4.750 0.6237 0.01406 0.00562 -0.0209 0.0890 1.0000
5.000 0.6462 0.01497 0.00648 -0.0200 0.0768 1.0000
5.250 0.6704 0.01561 0.00718 -0.0193 0.0695 1.0000
5.500 0.6920 0.01681 0.00831 -0.0183 0.0640 1.0000
5.750 0.7163 0.01755 0.00916 -0.0175 0.0596 1.0000
6.000 0.7401 0.01845 0.01008 -0.0168 0.0553 1.0000
6.250 0.7622 0.02045 0.01203 -0.0159 0.0514 1.0000
6.500 0.7873 0.02117 0.01295 -0.0152 0.0481 1.0000
6.750 0.8117 0.02252 0.01444 -0.0144 0.0453 1.0000
7.000 0.8354 0.02403 0.01605 -0.0137 0.0428 1.0000
7.250 0.8563 0.02726 0.01949 -0.0129 0.0400 1.0000
7.500 0.8785 0.02881 0.02142 -0.0118 0.0385 1.0000
7.750 0.8982 0.03150 0.02454 -0.0104 0.0377 1.0000
8.000 0.9148 0.03485 0.02835 -0.0088 0.0374 1.0000
8.250 0.9287 0.03813 0.03209 -0.0071 0.0364 1.0000
8.500 0.9386 0.04202 0.03647 -0.0053 0.0360 1.0000
8.750 0.9409 0.04755 0.04247 -0.0034 0.0378 1.0000
10.750 0.7903 0.11245 0.10898 -0.0295 0.0604 1.0000
11.000 0.7841 0.11851 0.11502 -0.0332 0.0581 1.0000
11.250 0.7830 0.12330 0.11979 -0.0354 0.0562 1.0000
11.500 0.7859 0.12710 0.12358 -0.0362 0.0545 1.0000
11.750 0.7937 0.12973 0.12623 -0.0353 0.0531 1.0000
12.000 0.6220 0.12861 0.12520 -0.0233 0.0608 1.0000
12.250 0.6156 0.13278 0.12937 -0.0253 0.0582 1.0000
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Polar data table (+)
Polar graphs
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