NACA M13 AIRFOIL (m13-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M13 AIRFOIL (m13-il) Reynolds number: 100,000 Max Cl/Cd: 56.73 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m13-il-100000.txt Download as CSV file: xf-m13-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M13 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4794 0.12001 0.11522 0.0031 1.0000 0.0496
-8.750 -0.4802 0.11842 0.11370 -0.0012 1.0000 0.0499
-8.500 -0.4803 0.11647 0.11181 -0.0060 1.0000 0.0500
-8.250 -0.4579 0.10701 0.10230 0.0013 1.0000 0.0524
-8.000 -0.4510 0.10356 0.09887 0.0004 1.0000 0.0543
-7.750 -0.4455 0.10037 0.09570 -0.0013 1.0000 0.0564
-7.500 -0.4414 0.09746 0.09284 -0.0039 1.0000 0.0585
-7.250 -0.4341 0.09529 0.09071 -0.0115 1.0000 0.0603
-7.000 -0.4182 0.09364 0.08898 -0.0229 1.0000 0.0610
-6.750 -0.4145 0.08674 0.08220 -0.0168 1.0000 0.0626
-6.500 -0.4048 0.08289 0.07838 -0.0155 1.0000 0.0659
-6.250 -0.3905 0.07946 0.07493 -0.0192 1.0000 0.0699
-6.000 -0.3566 0.07862 0.07377 -0.0338 1.0000 0.0732
-5.750 -0.3531 0.07192 0.06727 -0.0300 1.0000 0.0745
-5.500 -0.3423 0.06800 0.06341 -0.0289 1.0000 0.0771
-5.250 -0.3239 0.06465 0.06001 -0.0312 1.0000 0.0816
-5.000 -0.2947 0.06143 0.05654 -0.0378 1.0000 0.0866
-4.750 -0.2853 0.05751 0.05271 -0.0361 1.0000 0.0895
-4.500 -0.2553 0.05573 0.05057 -0.0407 1.0000 0.0995
-4.250 -0.2508 0.05162 0.04668 -0.0382 1.0000 0.1025
-4.000 -0.2393 0.04938 0.04441 -0.0374 1.0000 0.1083
-3.750 -0.2265 0.04741 0.04224 -0.0376 1.0000 0.1146
-3.500 -0.2234 0.04532 0.04021 -0.0353 1.0000 0.1178
-3.250 -0.2083 0.04426 0.03885 -0.0355 1.0000 0.1279
-3.000 -0.1671 0.04047 0.03492 -0.0404 0.9930 0.1430
-2.750 -0.1218 0.03762 0.03180 -0.0457 0.9845 0.1703
-2.500 -0.0803 0.03461 0.02865 -0.0500 0.9755 0.1987
-2.250 -0.0386 0.03159 0.02559 -0.0543 0.9684 0.2422
-2.000 -0.0036 0.02882 0.02287 -0.0569 0.9588 0.3053
-1.750 0.0318 0.02606 0.02016 -0.0590 0.9499 0.3771
-1.500 0.1244 0.02356 0.01541 -0.0657 0.9430 0.1106
-1.250 0.1667 0.02187 0.01315 -0.0673 0.9319 0.0985
-1.000 0.2046 0.02027 0.01136 -0.0689 0.9205 0.0966
-0.750 0.2397 0.01940 0.01021 -0.0696 0.9081 0.0992
-0.500 0.2703 0.01834 0.00917 -0.0698 0.8949 0.1039
-0.250 0.2987 0.01765 0.00841 -0.0693 0.8814 0.1062
0.000 0.3252 0.01709 0.00780 -0.0683 0.8677 0.1106
0.250 0.3498 0.01652 0.00730 -0.0670 0.8543 0.1190
0.500 0.3748 0.01608 0.00684 -0.0658 0.8412 0.1430
0.750 0.4115 0.01357 0.00639 -0.0670 0.8285 1.0000
1.000 0.4358 0.01377 0.00631 -0.0658 0.8148 1.0000
1.250 0.4602 0.01398 0.00634 -0.0647 0.8012 1.0000
1.500 0.4847 0.01420 0.00643 -0.0637 0.7879 1.0000
1.750 0.5094 0.01442 0.00654 -0.0629 0.7748 1.0000
2.000 0.5342 0.01466 0.00668 -0.0620 0.7620 1.0000
2.250 0.5592 0.01491 0.00685 -0.0612 0.7495 1.0000
2.500 0.5843 0.01516 0.00706 -0.0604 0.7373 1.0000
2.750 0.6095 0.01540 0.00725 -0.0596 0.7257 1.0000
3.000 0.6349 0.01566 0.00748 -0.0589 0.7135 1.0000
3.250 0.6604 0.01597 0.00779 -0.0583 0.7007 1.0000
3.500 0.6860 0.01628 0.00812 -0.0578 0.6881 1.0000
3.750 0.7115 0.01660 0.00851 -0.0573 0.6757 1.0000
4.000 0.7371 0.01691 0.00886 -0.0567 0.6637 1.0000
4.250 0.7628 0.01721 0.00921 -0.0561 0.6521 1.0000
4.500 0.7887 0.01747 0.00951 -0.0553 0.6413 1.0000
4.750 0.8144 0.01783 0.01004 -0.0549 0.6287 1.0000
5.000 0.8401 0.01821 0.01056 -0.0545 0.6162 1.0000
5.250 0.8655 0.01846 0.01096 -0.0537 0.6024 1.0000
5.500 0.8876 0.01758 0.00995 -0.0507 0.5686 1.0000
5.750 0.9094 0.01687 0.00922 -0.0482 0.5275 1.0000
6.000 0.9293 0.01638 0.00867 -0.0456 0.4584 1.0000
6.250 0.9301 0.01950 0.00963 -0.0421 0.1126 1.0000
6.500 0.9453 0.02179 0.01165 -0.0404 0.0756 1.0000
6.750 0.9626 0.02339 0.01333 -0.0389 0.0651 1.0000
7.000 0.9773 0.02522 0.01515 -0.0371 0.0587 1.0000
7.250 0.9959 0.02682 0.01682 -0.0354 0.0556 1.0000
7.500 1.0170 0.02867 0.01870 -0.0340 0.0533 1.0000
7.750 1.0409 0.03080 0.02083 -0.0329 0.0513 1.0000
8.000 1.0667 0.03470 0.02459 -0.0326 0.0480 1.0000
8.250 1.0904 0.03693 0.02715 -0.0316 0.0472 1.0000
8.500 1.1139 0.04060 0.03110 -0.0307 0.0476 1.0000
8.750 1.1363 0.04329 0.03416 -0.0294 0.0488 1.0000
9.000 1.1518 0.04617 0.03799 -0.0266 0.0534 1.0000
9.250 1.1654 0.05137 0.04367 -0.0250 0.0579 1.0000
9.500 1.1743 0.05685 0.04996 -0.0224 0.0695 1.0000
9.750 1.1155 0.05572 0.04957 -0.0147 0.0850 1.0000
10.250 1.0391 0.06543 0.06058 -0.0071 0.1046 1.0000
10.500 1.0103 0.06983 0.06511 -0.0060 0.1039 1.0000
10.750 0.9831 0.07483 0.07021 -0.0062 0.1027 1.0000
11.000 0.9582 0.07889 0.07427 -0.0069 0.0926 1.0000
11.250 0.9303 0.08487 0.08032 -0.0091 0.0902 1.0000
11.500 0.9039 0.09162 0.08712 -0.0118 0.0890 1.0000
11.750 0.8757 0.09931 0.09484 -0.0156 0.0883 1.0000
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Polar data table (+)
Polar graphs
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