MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 121 8.76% (mh121-il) Reynolds number: 100,000 Max Cl/Cd: 53.56 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh121-il-100000.txt Download as CSV file: xf-mh121-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 121 8.76%
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 -0.4282 0.10718 0.10242 -0.0378 1.0000 0.0762
-8.750 -0.4396 0.10509 0.10043 -0.0387 1.0000 0.0770
-8.500 -0.4545 0.10319 0.09866 -0.0391 1.0000 0.0774
-8.250 -0.4446 0.09865 0.09414 -0.0359 1.0000 0.0806
-8.000 -0.4448 0.09626 0.09179 -0.0337 1.0000 0.0835
-7.750 -0.4544 0.09417 0.08979 -0.0322 1.0000 0.0858
-7.500 -0.4712 0.09236 0.08808 -0.0305 1.0000 0.0878
-7.250 -0.4910 0.09081 0.08663 -0.0287 1.0000 0.0888
-7.000 -0.5095 0.08805 0.08397 -0.0313 1.0000 0.0900
-6.750 -0.5230 0.08366 0.07956 -0.0379 1.0000 0.0906
-6.500 -0.5181 0.08084 0.07686 -0.0309 1.0000 0.0940
-6.250 -0.5174 0.07802 0.07406 -0.0299 1.0000 0.0981
-6.000 -0.5261 0.07202 0.06759 -0.0451 1.0000 0.1044
-5.750 -0.5173 0.06887 0.06484 -0.0366 1.0000 0.1082
-5.500 -0.5107 0.06367 0.05937 -0.0432 1.0000 0.1188
-5.250 -0.5014 0.06109 0.05691 -0.0402 1.0000 0.1262
-5.000 -0.4893 0.05717 0.05289 -0.0421 1.0000 0.1392
-4.750 -0.4744 0.05308 0.04864 -0.0450 1.0000 0.1601
-4.000 -0.3477 0.03303 0.02547 -0.0579 1.0000 0.0535
-3.750 -0.3189 0.03012 0.02224 -0.0581 1.0000 0.0477
-3.500 -0.2884 0.02738 0.01898 -0.0582 1.0000 0.0438
-3.250 -0.2592 0.02532 0.01647 -0.0578 1.0000 0.0420
-3.000 -0.2319 0.02366 0.01462 -0.0573 1.0000 0.0424
-2.750 -0.2053 0.02233 0.01323 -0.0569 1.0000 0.0448
-2.500 -0.1787 0.02126 0.01219 -0.0569 1.0000 0.0590
-2.250 -0.1385 0.01753 0.01084 -0.0596 1.0000 0.5497
-2.000 -0.1256 0.01785 0.01137 -0.0555 1.0000 0.6679
-1.750 -0.1094 0.01803 0.01150 -0.0527 1.0000 0.7150
-1.500 -0.0958 0.01814 0.01162 -0.0493 1.0000 0.7584
-1.250 -0.0847 0.01817 0.01170 -0.0454 1.0000 0.8025
-1.000 -0.0716 0.01813 0.01156 -0.0422 1.0000 0.8416
-0.750 -0.0546 0.01805 0.01144 -0.0403 1.0000 0.8766
-0.500 -0.0320 0.01776 0.01117 -0.0399 1.0000 0.9446
-0.250 0.0000 0.01776 0.01095 -0.0429 1.0000 1.0000
0.000 0.0328 0.01814 0.01109 -0.0456 1.0000 1.0000
0.250 0.0616 0.01856 0.01129 -0.0472 1.0000 1.0000
0.500 0.0877 0.01900 0.01149 -0.0481 1.0000 1.0000
0.750 0.1123 0.01946 0.01181 -0.0487 1.0000 1.0000
1.000 0.1436 0.02009 0.01234 -0.0505 0.9968 1.0000
1.250 0.1836 0.02090 0.01305 -0.0540 0.9893 1.0000
1.500 0.2250 0.02180 0.01389 -0.0576 0.9825 1.0000
1.750 0.2601 0.02237 0.01445 -0.0600 0.9740 1.0000
2.000 0.2983 0.02307 0.01513 -0.0629 0.9660 1.0000
2.250 0.3376 0.02373 0.01580 -0.0660 0.9577 1.0000
2.500 0.3713 0.02421 0.01633 -0.0679 0.9478 1.0000
2.750 0.4077 0.02474 0.01697 -0.0702 0.9379 1.0000
3.000 0.4481 0.02526 0.01759 -0.0732 0.9283 1.0000
3.250 0.4917 0.02570 0.01814 -0.0765 0.9184 1.0000
3.500 0.5300 0.02596 0.01855 -0.0787 0.9061 1.0000
3.750 0.5728 0.02607 0.01885 -0.0814 0.8931 1.0000
4.000 0.6256 0.02578 0.01893 -0.0852 0.8789 1.0000
4.250 0.6744 0.02485 0.01831 -0.0875 0.8570 1.0000
4.500 0.7558 0.02191 0.01589 -0.0927 0.8305 1.0000
4.750 0.8391 0.01728 0.01185 -0.0957 0.7821 1.0000
5.000 0.8715 0.01627 0.00915 -0.0900 0.3626 1.0000
5.250 0.8613 0.02024 0.01116 -0.0837 0.1208 1.0000
5.500 0.8680 0.02311 0.01341 -0.0801 0.0505 1.0000
5.750 0.8885 0.02636 0.01648 -0.0784 0.0368 1.0000
6.000 0.9144 0.02770 0.01804 -0.0775 0.0288 1.0000
6.250 0.9467 0.03130 0.02174 -0.0781 0.0243 1.0000
6.500 0.9776 0.03462 0.02546 -0.0778 0.0239 1.0000
6.750 1.0025 0.03834 0.02963 -0.0766 0.0241 1.0000
7.000 1.0214 0.04280 0.03453 -0.0749 0.0246 1.0000
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Polar data table (+)
Polar graphs
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