NACA 8-H-12 AIRFOIL (n8h12-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 8-H-12 AIRFOIL (n8h12-il) Reynolds number: 50,000 Max Cl/Cd: 7.96 at α=-0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n8h12-il-50000.txt Download as CSV file: xf-n8h12-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 8-H-12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4328 0.11751 0.11197 0.0027 1.0000 0.2154
-9.500 -0.4072 0.11189 0.10636 0.0024 1.0000 0.2245
-9.250 -0.4291 0.11149 0.10612 -0.0034 1.0000 0.2324
-9.000 -0.3999 0.10582 0.10045 -0.0033 1.0000 0.2469
-8.750 -0.3805 0.10132 0.09598 -0.0045 1.0000 0.2596
-8.500 -0.3691 0.09774 0.09246 -0.0065 1.0000 0.2743
-8.250 -0.3599 0.09454 0.08933 -0.0084 1.0000 0.2923
-8.000 -0.3561 0.09189 0.08677 -0.0105 1.0000 0.3113
-7.750 -0.3608 0.08998 0.08497 -0.0118 1.0000 0.3294
-7.500 -0.3625 0.08813 0.08322 -0.0104 1.0000 0.3455
-7.250 -0.3639 0.08648 0.08165 -0.0069 1.0000 0.3592
-6.750 -0.3281 0.08019 0.07536 -0.0104 0.9770 0.4268
-6.500 -0.2669 0.07487 0.06995 -0.0124 0.9701 0.4884
-6.000 -0.1647 0.06616 0.06105 -0.0166 0.9508 0.6182
-5.250 -0.2822 0.04999 0.04313 -0.0578 0.8987 0.1794
-5.000 -0.2718 0.04745 0.04002 -0.0565 0.8880 0.1645
-4.750 -0.2575 0.04502 0.03714 -0.0552 0.8785 0.1561
-4.500 -0.2331 0.04289 0.03435 -0.0548 0.8702 0.1490
-4.250 -0.2206 0.04145 0.03260 -0.0528 0.8604 0.1468
-4.000 -0.2006 0.04013 0.03085 -0.0517 0.8522 0.1480
-3.750 -0.1791 0.03903 0.02930 -0.0506 0.8441 0.1503
-3.500 -0.1592 0.03815 0.02801 -0.0493 0.8362 0.1518
-3.250 -0.1307 0.03678 0.02657 -0.0496 0.8288 0.1571
-3.000 -0.1092 0.03628 0.02584 -0.0488 0.8216 0.1656
-2.750 0.1648 0.02789 0.02031 -0.0832 0.8159 1.0000
-2.500 0.1814 0.02850 0.02054 -0.0823 0.8086 1.0000
-2.250 0.1954 0.02921 0.02097 -0.0815 0.8007 1.0000
-2.000 0.2131 0.02986 0.02133 -0.0804 0.7944 1.0000
-1.750 0.2227 0.03082 0.02210 -0.0794 0.7877 1.0000
-1.500 0.2387 0.03160 0.02265 -0.0783 0.7818 1.0000
-1.250 0.2501 0.03257 0.02343 -0.0770 0.7763 1.0000
-1.000 0.2565 0.03364 0.02435 -0.0753 0.7705 1.0000
-0.750 0.2703 0.03460 0.02514 -0.0740 0.7661 1.0000
-0.500 0.2839 0.03565 0.02601 -0.0728 0.7621 1.0000
-0.250 0.2793 0.03699 0.02725 -0.0698 0.7583 1.0000
0.000 0.2802 0.03823 0.02836 -0.0672 0.7549 1.0000
0.250 0.2831 0.03947 0.02948 -0.0649 0.7528 1.0000
0.500 0.2856 0.04075 0.03063 -0.0624 0.7513 1.0000
0.750 0.2883 0.04200 0.03177 -0.0599 0.7500 1.0000
1.000 0.2787 0.04329 0.03295 -0.0559 0.7508 1.0000
1.250 0.2648 0.04464 0.03421 -0.0517 0.7554 1.0000
1.500 0.2677 0.04604 0.03550 -0.0497 0.7592 1.0000
1.750 0.2763 0.04753 0.03690 -0.0487 0.7643 1.0000
3.000 0.1440 0.04958 0.03869 -0.0227 0.9484 1.0000
3.250 0.1802 0.05204 0.04106 -0.0262 0.9290 1.0000
3.500 0.2126 0.05448 0.04343 -0.0289 0.9126 1.0000
3.750 0.2407 0.05675 0.04564 -0.0307 0.8976 1.0000
4.000 0.2570 0.05796 0.04682 -0.0304 0.8810 1.0000
4.250 0.2781 0.05974 0.04856 -0.0310 0.8662 1.0000
4.500 0.3010 0.06181 0.05061 -0.0319 0.8534 1.0000
4.750 0.3280 0.06431 0.05309 -0.0335 0.8408 1.0000
5.000 0.3493 0.06627 0.05506 -0.0340 0.8267 1.0000
5.250 0.3636 0.06764 0.05644 -0.0335 0.8127 1.0000
5.500 0.3779 0.06917 0.05798 -0.0331 0.7987 1.0000
5.750 0.3921 0.07085 0.05968 -0.0327 0.7856 1.0000
6.000 0.4091 0.07289 0.06174 -0.0328 0.7736 1.0000
6.250 0.4395 0.07618 0.06508 -0.0348 0.7626 1.0000
6.500 0.4542 0.07785 0.06679 -0.0345 0.7483 1.0000
6.750 0.4640 0.07930 0.06830 -0.0336 0.7341 1.0000
7.000 0.4742 0.08105 0.07009 -0.0330 0.7209 1.0000
7.250 0.4878 0.08320 0.07230 -0.0328 0.7080 1.0000
7.500 0.5074 0.08595 0.07512 -0.0334 0.6963 1.0000
7.750 0.5382 0.08967 0.07898 -0.0351 0.6831 1.0000
8.250 0.5505 0.09277 0.08221 -0.0333 0.6539 1.0000
8.500 0.5592 0.09488 0.08439 -0.0328 0.6397 1.0000
8.750 0.5694 0.09724 0.08684 -0.0326 0.6256 1.0000
9.000 0.5810 0.09977 0.08949 -0.0325 0.6111 1.0000
9.250 0.5928 0.10240 0.09222 -0.0325 0.5964 1.0000
9.500 0.6046 0.10505 0.09497 -0.0324 0.5810 1.0000
9.750 0.6157 0.10773 0.09776 -0.0323 0.5651 1.0000
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Polar data table (+)
Polar graphs
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