MH 120 11.57% (mh120-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MH 120 11.57% (mh120-il) Reynolds number: 500,000 Max Cl/Cd: 104.62 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh120-il-500000.txt Download as CSV file: xf-mh120-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 120 11.57%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4236 0.08581 0.08365 -0.0409 1.0000 0.0168
-9.250 -0.4278 0.08200 0.07987 -0.0422 1.0000 0.0173
-9.000 -0.4357 0.07761 0.07553 -0.0438 1.0000 0.0175
-8.750 -0.4505 0.07242 0.07040 -0.0462 1.0000 0.0176
-8.500 -0.4798 0.06691 0.06493 -0.0494 1.0000 0.0173
-8.250 -0.5051 0.06249 0.06047 -0.0490 0.9983 0.0172
-8.000 -0.4948 0.05491 0.05267 -0.0563 0.9914 0.0176
-7.750 -0.4818 0.04877 0.04628 -0.0609 0.9858 0.0183
-7.500 -0.4590 0.04587 0.04295 -0.0622 0.9786 0.0211
-7.250 -0.4401 0.04211 0.03879 -0.0640 0.9740 0.0212
-7.000 -0.3930 0.01894 0.01563 -0.0690 0.9613 0.0237
-6.750 -0.3726 0.01657 0.01307 -0.0695 0.9547 0.0250
-6.500 -0.3451 0.01453 0.01073 -0.0704 0.9498 0.0282
-6.250 -0.3247 0.01105 0.00679 -0.0711 0.9439 0.0322
-5.250 -0.2435 0.01687 0.01122 -0.0690 0.9277 0.0263
-5.000 -0.2080 0.01466 0.00864 -0.0698 0.9206 0.0224
-4.750 -0.1773 0.01342 0.00729 -0.0704 0.9114 0.0227
-4.500 -0.1450 0.01250 0.00627 -0.0714 0.9025 0.0228
-4.250 -0.1196 0.01180 0.00548 -0.0708 0.8909 0.0230
-4.000 -0.0959 0.01124 0.00487 -0.0700 0.8787 0.0245
-3.750 -0.0722 0.01079 0.00432 -0.0690 0.8666 0.0249
-3.500 -0.0489 0.01038 0.00380 -0.0679 0.8546 0.0257
-3.250 -0.0251 0.01006 0.00338 -0.0669 0.8427 0.0267
-3.000 -0.0008 0.00982 0.00302 -0.0660 0.8311 0.0280
-2.750 0.0228 0.00963 0.00273 -0.0650 0.8188 0.0294
-2.500 0.0462 0.00943 0.00245 -0.0639 0.8069 0.0350
-2.250 0.0649 0.00886 0.00219 -0.0620 0.7953 0.1312
-2.000 0.0772 0.00787 0.00201 -0.0593 0.7839 0.3634
-1.750 0.0944 0.00743 0.00194 -0.0571 0.7732 0.4868
-1.500 0.1115 0.00712 0.00189 -0.0547 0.7624 0.5808
-1.250 0.1265 0.00680 0.00189 -0.0518 0.7520 0.6779
-1.000 0.1446 0.00654 0.00189 -0.0494 0.7423 0.7633
-0.750 0.1890 0.00629 0.00193 -0.0529 0.7333 0.8705
-0.500 0.2817 0.00640 0.00204 -0.0673 0.7239 0.9241
-0.250 0.3235 0.00656 0.00213 -0.0702 0.7143 0.9375
0.000 0.3588 0.00674 0.00222 -0.0718 0.7048 0.9490
0.250 0.3940 0.00692 0.00234 -0.0733 0.6948 0.9585
0.500 0.4321 0.00710 0.00244 -0.0755 0.6850 0.9649
0.750 0.4656 0.00728 0.00254 -0.0767 0.6751 0.9737
1.000 0.5067 0.00739 0.00260 -0.0797 0.6643 0.9780
1.250 0.5431 0.00753 0.00268 -0.0816 0.6524 0.9844
1.500 0.5827 0.00761 0.00271 -0.0843 0.6411 0.9886
1.750 0.6218 0.00769 0.00273 -0.0869 0.6304 0.9932
2.000 0.6612 0.00772 0.00273 -0.0896 0.6199 0.9972
2.250 0.6980 0.00772 0.00272 -0.0918 0.6089 1.0000
2.500 0.7177 0.00778 0.00274 -0.0902 0.5987 1.0000
2.750 0.7376 0.00786 0.00278 -0.0887 0.5888 1.0000
3.000 0.7579 0.00792 0.00284 -0.0872 0.5775 1.0000
3.250 0.7785 0.00799 0.00290 -0.0857 0.5671 1.0000
3.500 0.7990 0.00808 0.00297 -0.0843 0.5561 1.0000
3.750 0.8193 0.00818 0.00305 -0.0828 0.5443 1.0000
4.000 0.8395 0.00829 0.00313 -0.0812 0.5314 1.0000
4.250 0.8602 0.00840 0.00325 -0.0798 0.5190 1.0000
4.500 0.8810 0.00851 0.00337 -0.0784 0.5065 1.0000
4.750 0.9011 0.00865 0.00350 -0.0768 0.4917 1.0000
5.000 0.9208 0.00882 0.00364 -0.0752 0.4758 1.0000
5.250 0.9405 0.00899 0.00380 -0.0736 0.4579 1.0000
5.500 0.9580 0.00924 0.00397 -0.0715 0.4306 1.0000
5.750 0.9743 0.00957 0.00418 -0.0692 0.3959 1.0000
6.000 0.9886 0.01001 0.00444 -0.0667 0.3536 1.0000
6.250 1.0010 0.01058 0.00478 -0.0638 0.3057 1.0000
6.500 1.0116 0.01129 0.00520 -0.0607 0.2528 1.0000
6.750 1.0250 0.01187 0.00563 -0.0580 0.2167 1.0000
7.000 1.0367 0.01256 0.00610 -0.0552 0.1754 1.0000
7.250 1.0461 0.01337 0.00665 -0.0520 0.1297 1.0000
7.500 1.0507 0.01443 0.00736 -0.0479 0.0760 1.0000
7.750 1.0548 0.01550 0.00815 -0.0438 0.0337 1.0000
8.000 1.0589 0.01651 0.00904 -0.0395 0.0143 1.0000
8.250 1.0682 0.01709 0.00968 -0.0360 0.0123 1.0000
8.500 1.0776 0.01770 0.01037 -0.0327 0.0113 1.0000
8.750 1.0848 0.01847 0.01125 -0.0291 0.0106 1.0000
9.000 1.0924 0.01928 0.01215 -0.0258 0.0103 1.0000
9.250 1.1023 0.02002 0.01297 -0.0230 0.0099 1.0000
9.500 1.1113 0.02084 0.01387 -0.0203 0.0095 1.0000
9.750 1.1203 0.02173 0.01483 -0.0177 0.0088 1.0000
10.000 1.1265 0.02282 0.01603 -0.0149 0.0088 1.0000
10.250 1.1321 0.02403 0.01732 -0.0123 0.0086 1.0000
10.500 1.1366 0.02538 0.01873 -0.0098 0.0080 1.0000
10.750 1.1412 0.02682 0.02031 -0.0074 0.0082 1.0000
11.000 1.1452 0.02839 0.02197 -0.0053 0.0081 1.0000
11.250 1.1471 0.03022 0.02387 -0.0032 0.0077 1.0000
11.500 1.1518 0.03193 0.02570 -0.0015 0.0079 1.0000
11.750 1.1549 0.03386 0.02771 0.0002 0.0077 1.0000
12.000 1.1571 0.03597 0.02991 0.0018 0.0076 1.0000
12.250 1.1647 0.03766 0.03174 0.0030 0.0079 1.0000
12.500 1.1658 0.04009 0.03426 0.0046 0.0076 1.0000
12.750 1.1698 0.04233 0.03663 0.0059 0.0076 1.0000
13.000 1.1708 0.04547 0.03992 0.0079 0.0073 1.0000
13.250 1.1744 0.04771 0.04229 0.0087 0.0074 1.0000
13.500 1.1761 0.05019 0.04495 0.0095 0.0075 1.0000
13.750 1.1760 0.05294 0.04792 0.0101 0.0078 1.0000
14.000 1.1555 0.05941 0.05494 0.0117 0.0089 1.0000
14.250 1.1424 0.06414 0.05990 0.0118 0.0093 1.0000
14.500 1.1243 0.06971 0.06571 0.0112 0.0096 1.0000
14.750 1.1038 0.07586 0.07206 0.0100 0.0100 1.0000
15.000 0.9736 0.07262 0.06891 0.0163 0.0087 1.0000
15.250 0.9511 0.07916 0.07565 0.0150 0.0089 1.0000
15.500 0.9280 0.08570 0.08237 0.0132 0.0091 1.0000
15.750 0.9077 0.09161 0.08844 0.0111 0.0092 1.0000
16.000 0.8834 0.09785 0.09484 0.0086 0.0093 1.0000
16.250 0.8551 0.10316 0.10029 0.0062 0.0093 1.0000
16.500 0.8320 0.10838 0.10564 0.0034 0.0094 1.0000
16.750 0.8075 0.11446 0.11186 0.0000 0.0094 1.0000
17.000 0.7869 0.12033 0.11784 -0.0035 0.0095 1.0000
17.250 0.7621 0.12729 0.12492 -0.0076 0.0096 1.0000
17.500 0.7379 0.13459 0.13233 -0.0119 0.0097 1.0000
17.750 0.7107 0.14299 0.14081 -0.0166 0.0098 1.0000
18.000 0.6756 0.15368 0.15156 -0.0219 0.0102 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 120 11.57% (mh120-il)