NACA 65(1)-412 (naca651412-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(1)-412 (naca651412-il) Reynolds number: 200,000 Max Cl/Cd: 74.87 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca651412-il-200000.txt Download as CSV file: xf-naca651412-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(1)-412
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 -0.4253 0.08907 0.08554 -0.0515 1.0000 0.0529
-9.500 -0.4361 0.08422 0.08077 -0.0545 1.0000 0.0541
-9.250 -0.4572 0.07845 0.07507 -0.0589 1.0000 0.0548
-9.000 -0.4766 0.07540 0.07210 -0.0580 1.0000 0.0544
-8.750 -0.5048 0.07399 0.07077 -0.0538 1.0000 0.0538
-8.500 -0.5373 0.07341 0.07028 -0.0481 1.0000 0.0526
-8.250 -0.5424 0.06711 0.06375 -0.0562 0.9923 0.0545
-8.000 -0.5460 0.05979 0.05574 -0.0647 0.9809 0.0573
-7.750 -0.5200 0.05600 0.05223 -0.0660 0.9781 0.0600
-7.500 -0.4972 0.05249 0.04857 -0.0693 0.9730 0.0639
-7.250 -0.4856 0.04793 0.04331 -0.0725 0.9638 0.0711
-7.000 -0.4584 0.04436 0.03984 -0.0748 0.9602 0.0740
-6.750 -0.4302 0.04124 0.03613 -0.0783 0.9564 0.0853
-6.500 -0.4086 0.03836 0.03334 -0.0788 0.9496 0.0889
-6.250 -0.3801 0.03575 0.03047 -0.0812 0.9452 0.1022
-6.000 -0.3385 0.02790 0.02125 -0.0809 0.9428 0.0532
-5.750 -0.3078 0.02440 0.01719 -0.0812 0.9385 0.0480
-5.500 -0.2786 0.02266 0.01519 -0.0815 0.9327 0.0482
-5.250 -0.2433 0.02128 0.01368 -0.0831 0.9295 0.0504
-5.000 -0.2064 0.01978 0.01201 -0.0846 0.9270 0.0511
-4.750 -0.1816 0.01882 0.01098 -0.0840 0.9199 0.0523
-4.500 -0.1505 0.01794 0.01002 -0.0845 0.9153 0.0547
-4.250 -0.1185 0.01685 0.00890 -0.0854 0.9120 0.0582
-4.000 -0.0973 0.01612 0.00822 -0.0844 0.9041 0.0615
-3.750 -0.0684 0.01546 0.00754 -0.0848 0.8992 0.0665
-3.500 -0.0406 0.01480 0.00686 -0.0850 0.8945 0.0760
-3.250 -0.0173 0.01426 0.00635 -0.0845 0.8872 0.0960
-3.000 -0.0015 0.01177 0.00606 -0.0836 0.8823 0.6206
-2.750 0.0208 0.01198 0.00634 -0.0819 0.8754 0.6804
-2.500 0.0464 0.01217 0.00653 -0.0808 0.8701 0.7127
-2.250 0.0706 0.01253 0.00692 -0.0787 0.8665 0.7476
-2.000 0.0864 0.01306 0.00753 -0.0751 0.8590 0.7756
-1.750 0.1081 0.01334 0.00780 -0.0727 0.8542 0.7945
-1.500 0.1336 0.01341 0.00781 -0.0717 0.8499 0.8053
-1.250 0.1579 0.01344 0.00779 -0.0712 0.8433 0.8119
-1.000 0.1867 0.01336 0.00764 -0.0715 0.8390 0.8178
-0.750 0.2136 0.01334 0.00757 -0.0712 0.8347 0.8230
-0.500 0.2396 0.01337 0.00756 -0.0713 0.8283 0.8303
-0.250 0.2662 0.01333 0.00749 -0.0708 0.8242 0.8349
0.000 0.2939 0.01332 0.00745 -0.0708 0.8202 0.8410
0.250 0.3180 0.01340 0.00753 -0.0704 0.8138 0.8474
0.500 0.3446 0.01338 0.00750 -0.0701 0.8096 0.8531
1.000 0.3948 0.01349 0.00764 -0.0693 0.7994 0.8660
1.250 0.4222 0.01349 0.00764 -0.0693 0.7951 0.8733
1.500 0.4497 0.01346 0.00761 -0.0690 0.7919 0.8793
1.750 0.4708 0.01364 0.00787 -0.0681 0.7852 0.8874
2.000 0.4957 0.01364 0.00791 -0.0674 0.7807 0.8944
2.250 0.5237 0.01362 0.00790 -0.0673 0.7774 0.9025
2.500 0.5428 0.01377 0.00814 -0.0658 0.7705 0.9110
2.750 0.5686 0.01373 0.00816 -0.0654 0.7655 0.9200
3.000 0.5951 0.01363 0.00809 -0.0648 0.7612 0.9289
3.250 0.6155 0.01368 0.00826 -0.0635 0.7534 0.9399
3.500 0.6469 0.01342 0.00802 -0.0638 0.7479 0.9490
3.750 0.6745 0.01317 0.00785 -0.0635 0.7364 0.9599
4.000 0.7114 0.01250 0.00717 -0.0643 0.7196 0.9676
4.250 0.7468 0.01180 0.00643 -0.0648 0.6921 0.9764
4.500 0.7840 0.01146 0.00614 -0.0664 0.6673 0.9856
4.750 0.8222 0.01126 0.00596 -0.0684 0.6373 0.9957
5.000 0.8393 0.01121 0.00587 -0.0665 0.6017 1.0000
5.250 0.8502 0.01141 0.00580 -0.0634 0.5177 1.0000
5.500 0.8384 0.01351 0.00651 -0.0573 0.2827 1.0000
5.750 0.8285 0.01635 0.00806 -0.0525 0.0877 1.0000
6.000 0.8418 0.01757 0.00912 -0.0506 0.0654 1.0000
6.250 0.8576 0.01853 0.01007 -0.0491 0.0570 1.0000
6.500 0.8699 0.01960 0.01118 -0.0469 0.0528 1.0000
6.750 0.8852 0.02054 0.01217 -0.0452 0.0491 1.0000
7.000 0.8996 0.02167 0.01326 -0.0435 0.0455 1.0000
7.250 0.9165 0.02324 0.01481 -0.0422 0.0431 1.0000
7.500 0.9403 0.02440 0.01604 -0.0417 0.0416 1.0000
7.750 0.9691 0.02581 0.01751 -0.0420 0.0401 1.0000
8.000 1.0037 0.02756 0.01936 -0.0433 0.0389 1.0000
8.250 1.0336 0.02918 0.02106 -0.0438 0.0374 1.0000
8.500 1.0621 0.03099 0.02292 -0.0444 0.0357 1.0000
8.750 1.0935 0.03356 0.02565 -0.0452 0.0352 1.0000
9.000 1.1201 0.03618 0.02857 -0.0451 0.0353 1.0000
9.250 1.1396 0.04014 0.03323 -0.0432 0.0378 1.0000
9.500 1.1535 0.04584 0.03944 -0.0415 0.0417 1.0000
13.000 0.7063 0.13445 0.13161 -0.0444 0.0740 1.0000
13.250 0.7034 0.13834 0.13551 -0.0465 0.0714 1.0000
13.500 0.7097 0.14085 0.13805 -0.0469 0.0694 1.0000
13.750 0.8650 0.15209 0.14887 -0.0572 0.0587 1.0000
14.000 0.8734 0.15510 0.15190 -0.0578 0.0570 1.0000
14.250 0.8905 0.15599 0.15284 -0.0554 0.0556 1.0000
14.500 0.6889 0.15948 0.15668 -0.0587 0.0601 1.0000
14.750 0.6980 0.16170 0.15891 -0.0591 0.0572 1.0000
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