NACA 747A415 (naca747a415-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 747A415 (naca747a415-il) Reynolds number: 200,000 Max Cl/Cd: 73.77 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca747a415-il-200000.txt Download as CSV file: xf-naca747a415-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 747A415
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4329 0.07682 0.07348 -0.0728 0.9470 0.0684
-10.000 -0.4675 0.07348 0.06987 -0.0731 0.9152 0.0686
-9.750 -0.4969 0.07198 0.06810 -0.0693 0.8933 0.0689
-9.500 -0.4420 0.06543 0.06190 -0.0725 0.8891 0.0717
-9.250 -0.4487 0.06322 0.05960 -0.0704 0.8740 0.0728
-9.000 -0.4573 0.06101 0.05727 -0.0680 0.8610 0.0743
-8.750 -0.4662 0.05837 0.05444 -0.0658 0.8500 0.0760
-8.500 -0.5015 0.05870 0.05400 -0.0602 0.8363 0.0811
-8.250 -0.4976 0.05200 0.04731 -0.0600 0.8281 0.0829
-8.000 -0.4817 0.04927 0.04459 -0.0594 0.8198 0.0846
-7.750 -0.4696 0.04710 0.04233 -0.0582 0.8112 0.0869
-7.500 -0.4844 0.03650 0.03033 -0.0519 0.8042 0.0557
-7.250 -0.4711 0.03337 0.02683 -0.0500 0.7972 0.0540
-7.000 -0.4558 0.03004 0.02297 -0.0479 0.7894 0.0521
-6.750 -0.4373 0.02725 0.01953 -0.0459 0.7836 0.0506
-6.500 -0.4131 0.02562 0.01770 -0.0453 0.7756 0.0511
-6.250 -0.3884 0.02439 0.01631 -0.0448 0.7693 0.0523
-6.000 -0.3632 0.02341 0.01518 -0.0443 0.7628 0.0543
-5.750 -0.3371 0.02236 0.01394 -0.0438 0.7559 0.0559
-5.500 -0.3106 0.02144 0.01277 -0.0433 0.7506 0.0573
-5.250 -0.2829 0.02017 0.01144 -0.0433 0.7439 0.0592
-5.000 -0.2570 0.01931 0.01062 -0.0430 0.7378 0.0625
-4.750 -0.2314 0.01874 0.00994 -0.0425 0.7330 0.0663
-4.500 -0.2057 0.01810 0.00927 -0.0421 0.7261 0.0695
-4.250 -0.1828 0.01728 0.00852 -0.0414 0.7206 0.0748
-4.000 -0.1587 0.01688 0.00802 -0.0406 0.7162 0.0817
-3.750 -0.1371 0.01625 0.00750 -0.0397 0.7101 0.0914
-3.500 -0.1151 0.01572 0.00701 -0.0388 0.7051 0.1075
-3.250 -0.0960 0.01492 0.00649 -0.0374 0.7011 0.1598
-3.000 -0.0962 0.01286 0.00607 -0.0334 0.6967 0.4991
-2.750 -0.0839 0.01281 0.00711 -0.0285 0.6918 0.7713
-2.500 -0.0610 0.01341 0.00764 -0.0262 0.6876 0.8134
-2.250 -0.0360 0.01404 0.00816 -0.0242 0.6843 0.8372
-2.000 -0.0084 0.01471 0.00875 -0.0228 0.6805 0.8548
-1.750 0.0205 0.01526 0.00925 -0.0219 0.6759 0.8702
-1.500 0.0604 0.01593 0.00982 -0.0226 0.6721 0.8865
-1.250 0.1696 0.01725 0.01093 -0.0352 0.6690 0.9162
-1.000 0.2264 0.01728 0.01079 -0.0407 0.6664 0.9219
-0.750 0.2518 0.01732 0.01083 -0.0406 0.6626 0.9288
-0.500 0.2839 0.01727 0.01073 -0.0419 0.6590 0.9330
-0.250 0.3206 0.01720 0.01061 -0.0440 0.6559 0.9369
0.000 0.3490 0.01721 0.01055 -0.0445 0.6533 0.9427
0.250 0.3845 0.01715 0.01042 -0.0463 0.6510 0.9478
0.500 0.4214 0.01715 0.01039 -0.0485 0.6480 0.9524
0.750 0.4466 0.01724 0.01051 -0.0486 0.6446 0.9573
1.000 0.4767 0.01724 0.01052 -0.0496 0.6417 0.9606
1.250 0.5097 0.01721 0.01048 -0.0511 0.6392 0.9630
1.500 0.5396 0.01721 0.01047 -0.0521 0.6370 0.9658
1.750 0.5664 0.01724 0.01047 -0.0523 0.6349 0.9684
2.000 0.5895 0.01740 0.01063 -0.0519 0.6325 0.9713
2.250 0.6181 0.01754 0.01086 -0.0528 0.6295 0.9732
2.500 0.6481 0.01763 0.01102 -0.0540 0.6264 0.9751
2.750 0.6773 0.01770 0.01112 -0.0548 0.6235 0.9774
3.000 0.7045 0.01774 0.01118 -0.0552 0.6209 0.9793
3.250 0.7311 0.01779 0.01122 -0.0553 0.6186 0.9812
3.500 0.7552 0.01802 0.01149 -0.0552 0.6160 0.9835
3.750 0.7830 0.01827 0.01188 -0.0561 0.6121 0.9851
4.000 0.8112 0.01842 0.01211 -0.0568 0.6086 0.9867
4.250 0.8407 0.01848 0.01222 -0.0576 0.6055 0.9887
4.500 0.8695 0.01849 0.01226 -0.0582 0.6029 0.9904
4.750 0.8960 0.01864 0.01245 -0.0583 0.5999 0.9919
5.000 0.9193 0.01889 0.01286 -0.0583 0.5937 0.9939
5.250 0.9513 0.01855 0.01254 -0.0591 0.5883 0.9955
5.500 0.9813 0.01833 0.01233 -0.0596 0.5833 0.9970
5.750 1.0078 0.01808 0.01218 -0.0596 0.5741 0.9987
6.000 1.0365 0.01748 0.01157 -0.0595 0.5638 1.0000
6.250 1.0603 0.01689 0.01092 -0.0584 0.5539 1.0000
6.500 1.0779 0.01669 0.01083 -0.0566 0.5427 1.0000
6.750 1.0983 0.01640 0.01056 -0.0552 0.5325 1.0000
7.000 1.1185 0.01612 0.01029 -0.0537 0.5219 1.0000
7.250 1.1338 0.01607 0.01038 -0.0517 0.5101 1.0000
7.500 1.1492 0.01598 0.01037 -0.0495 0.4969 1.0000
7.750 1.1625 0.01591 0.01038 -0.0470 0.4810 1.0000
8.000 1.1730 0.01590 0.01042 -0.0441 0.4608 1.0000
8.250 1.1779 0.01601 0.01060 -0.0403 0.4327 1.0000
8.500 1.1710 0.01629 0.01070 -0.0344 0.3815 1.0000
8.750 1.1488 0.01685 0.01100 -0.0261 0.3446 1.0000
9.000 1.1202 0.01728 0.01131 -0.0167 0.3244 1.0000
9.250 1.0960 0.01843 0.01221 -0.0095 0.2873 1.0000
9.500 1.0784 0.02036 0.01386 -0.0048 0.2432 1.0000
9.750 1.0600 0.02287 0.01607 -0.0011 0.1976 1.0000
10.000 1.0428 0.02572 0.01862 0.0018 0.1529 1.0000
10.250 1.0265 0.02880 0.02141 0.0042 0.1132 1.0000
10.500 1.0138 0.03181 0.02420 0.0061 0.0869 1.0000
10.750 1.0080 0.03442 0.02672 0.0076 0.0729 1.0000
11.000 1.0047 0.03689 0.02913 0.0087 0.0648 1.0000
11.250 1.0053 0.03910 0.03134 0.0097 0.0586 1.0000
11.500 1.0062 0.04133 0.03357 0.0105 0.0549 1.0000
11.750 1.0113 0.04326 0.03555 0.0112 0.0513 1.0000
12.000 1.0126 0.04551 0.03775 0.0120 0.0483 1.0000
12.250 1.0197 0.04728 0.03957 0.0127 0.0461 1.0000
12.500 1.0284 0.04895 0.04129 0.0133 0.0436 1.0000
12.750 1.0379 0.05051 0.04284 0.0139 0.0420 1.0000
13.000 1.0502 0.05176 0.04401 0.0150 0.0399 1.0000
13.250 1.0626 0.05320 0.04557 0.0155 0.0381 1.0000
13.500 1.0775 0.05441 0.04684 0.0162 0.0369 1.0000
13.750 1.0938 0.05554 0.04800 0.0168 0.0357 1.0000
14.000 1.1137 0.05647 0.04893 0.0176 0.0348 1.0000
14.250 1.1499 0.05685 0.04926 0.0188 0.0335 1.0000
14.500 1.1602 0.05883 0.05146 0.0192 0.0331 1.0000
14.750 1.1684 0.06105 0.05390 0.0195 0.0325 1.0000
15.000 1.1763 0.06344 0.05649 0.0197 0.0320 1.0000
15.250 1.1814 0.06612 0.05938 0.0199 0.0315 1.0000
15.500 1.1832 0.06904 0.06250 0.0198 0.0309 1.0000
15.750 1.1839 0.07236 0.06605 0.0198 0.0309 1.0000
16.000 1.1802 0.07610 0.07002 0.0194 0.0306 1.0000
16.250 1.1723 0.08041 0.07458 0.0188 0.0307 1.0000
16.500 1.1611 0.08514 0.07958 0.0179 0.0307 1.0000
16.750 1.1454 0.09073 0.08544 0.0164 0.0310 1.0000
17.000 1.1275 0.09669 0.09165 0.0144 0.0311 1.0000
17.250 1.1061 0.10346 0.09865 0.0118 0.0314 1.0000
17.500 1.0841 0.11062 0.10604 0.0086 0.0317 1.0000
17.750 1.0600 0.11855 0.11418 0.0046 0.0321 1.0000
18.000 1.0342 0.12729 0.12311 -0.0002 0.0324 1.0000
18.250 1.0088 0.13661 0.13260 -0.0056 0.0328 1.0000
18.500 0.9913 0.14490 0.14099 -0.0103 0.0333 1.0000
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