MH 120 11.57% (mh120-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 120 11.57% (mh120-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.87 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh120-il-1000000-n5.txt Download as CSV file: xf-mh120-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4931 0.09305 0.09145 -0.0365 1.0000 0.0047
-11.000 -0.5047 0.08670 0.08513 -0.0392 1.0000 0.0050
-10.500 -0.7637 0.03053 0.02783 -0.0639 0.9866 0.0050
-10.250 -0.7510 0.02857 0.02568 -0.0632 0.9792 0.0051
-10.000 -0.7271 0.02792 0.02494 -0.0636 0.9740 0.0052
-9.750 -0.7083 0.02619 0.02302 -0.0636 0.9678 0.0053
-9.500 -0.6822 0.02526 0.02198 -0.0644 0.9628 0.0054
-9.250 -0.6513 0.02464 0.02128 -0.0660 0.9590 0.0056
-9.000 -0.6246 0.02320 0.01966 -0.0671 0.9521 0.0058
-8.750 -0.5948 0.02118 0.01737 -0.0689 0.9460 0.0060
-8.500 -0.5627 0.01965 0.01560 -0.0709 0.9384 0.0065
-8.250 -0.5214 0.01905 0.01486 -0.0745 0.9323 0.0071
-8.000 -0.4869 0.01782 0.01340 -0.0767 0.9225 0.0075
-7.750 -0.4528 0.01699 0.01240 -0.0786 0.9118 0.0078
-7.500 -0.4227 0.01620 0.01143 -0.0796 0.8999 0.0079
-7.250 -0.3960 0.01547 0.01054 -0.0798 0.8873 0.0080
-7.000 -0.3744 0.01429 0.00915 -0.0789 0.8743 0.0083
-6.750 -0.3542 0.01334 0.00805 -0.0777 0.8609 0.0088
-6.500 -0.3322 0.01287 0.00751 -0.0767 0.8479 0.0091
-6.250 -0.3101 0.01248 0.00703 -0.0756 0.8349 0.0093
-6.000 -0.2882 0.01215 0.00661 -0.0745 0.8211 0.0097
-5.750 -0.2670 0.01175 0.00611 -0.0731 0.8072 0.0100
-5.500 -0.2453 0.01143 0.00570 -0.0719 0.7937 0.0103
-5.250 -0.2241 0.01110 0.00526 -0.0705 0.7803 0.0107
-5.000 -0.2029 0.01076 0.00482 -0.0691 0.7672 0.0109
-4.750 -0.1815 0.01045 0.00443 -0.0678 0.7551 0.0111
-4.500 -0.1601 0.01016 0.00405 -0.0664 0.7430 0.0114
-4.250 -0.1385 0.00989 0.00369 -0.0651 0.7320 0.0115
-4.000 -0.1161 0.00967 0.00339 -0.0639 0.7214 0.0118
-3.750 -0.0932 0.00946 0.00312 -0.0629 0.7115 0.0121
-3.500 -0.0702 0.00927 0.00285 -0.0618 0.7023 0.0124
-3.250 -0.0474 0.00906 0.00257 -0.0607 0.6929 0.0124
-3.000 -0.0238 0.00889 0.00234 -0.0598 0.6839 0.0126
-2.750 0.0000 0.00875 0.00214 -0.0589 0.6757 0.0128
-2.500 0.0241 0.00863 0.00197 -0.0581 0.6671 0.0129
-2.250 0.0478 0.00847 0.00173 -0.0572 0.6586 0.0141
-1.750 0.0968 0.00829 0.00146 -0.0557 0.6421 0.0163
-1.500 0.1215 0.00824 0.00138 -0.0550 0.6342 0.0171
-1.250 0.1465 0.00819 0.00129 -0.0543 0.6259 0.0184
-1.000 0.1713 0.00815 0.00123 -0.0537 0.6180 0.0232
-0.750 0.1891 0.00759 0.00110 -0.0517 0.6101 0.1760
-0.500 0.2068 0.00705 0.00103 -0.0498 0.6030 0.3303
-0.250 0.2271 0.00675 0.00102 -0.0484 0.5951 0.4257
0.000 0.2503 0.00664 0.00101 -0.0474 0.5868 0.4718
0.250 0.2714 0.00646 0.00102 -0.0460 0.5784 0.5417
0.500 0.2936 0.00633 0.00103 -0.0448 0.5702 0.5955
0.750 0.3137 0.00618 0.00105 -0.0432 0.5608 0.6608
1.000 0.3275 0.00589 0.00109 -0.0400 0.5508 0.7719
1.250 0.3495 0.00577 0.00113 -0.0387 0.5394 0.8290
1.500 0.3874 0.00570 0.00119 -0.0410 0.5279 0.8816
1.750 0.4672 0.00577 0.00128 -0.0532 0.5141 0.9200
2.000 0.5230 0.00590 0.00139 -0.0598 0.5017 0.9359
2.250 0.5679 0.00608 0.00152 -0.0637 0.4888 0.9472
2.500 0.6042 0.00624 0.00164 -0.0657 0.4763 0.9550
2.750 0.6361 0.00640 0.00177 -0.0667 0.4644 0.9622
3.000 0.6643 0.00657 0.00188 -0.0669 0.4503 0.9699
3.250 0.6938 0.00675 0.00201 -0.0674 0.4342 0.9762
3.500 0.7226 0.00694 0.00215 -0.0677 0.4170 0.9818
3.750 0.7501 0.00717 0.00230 -0.0679 0.3968 0.9860
4.000 0.7813 0.00738 0.00244 -0.0688 0.3772 0.9887
4.250 0.8100 0.00772 0.00263 -0.0693 0.3423 0.9918
4.750 0.8641 0.00884 0.00323 -0.0700 0.2327 0.9974
5.000 0.8948 0.00924 0.00347 -0.0711 0.2012 0.9992
5.250 0.9178 0.00976 0.00377 -0.0705 0.1577 1.0000
5.500 0.9319 0.01028 0.00410 -0.0680 0.1199 1.0000
5.750 0.9448 0.01088 0.00448 -0.0652 0.0798 1.0000
6.000 0.9541 0.01169 0.00503 -0.0618 0.0318 1.0000
6.250 0.9672 0.01230 0.00551 -0.0590 0.0083 1.0000
6.500 0.9856 0.01262 0.00583 -0.0572 0.0058 1.0000
6.750 1.0046 0.01290 0.00614 -0.0556 0.0052 1.0000
7.000 1.0231 0.01321 0.00648 -0.0539 0.0047 1.0000
7.250 1.0419 0.01349 0.00679 -0.0522 0.0047 1.0000
7.500 1.0592 0.01386 0.00720 -0.0503 0.0042 1.0000
7.750 1.0766 0.01422 0.00762 -0.0484 0.0041 1.0000
8.000 1.0924 0.01465 0.00809 -0.0463 0.0034 1.0000
8.250 1.1076 0.01511 0.00858 -0.0440 0.0031 1.0000
8.500 1.1185 0.01568 0.00922 -0.0409 0.0029 1.0000
8.750 1.1299 0.01609 0.00968 -0.0379 0.0030 1.0000
9.000 1.1389 0.01665 0.01032 -0.0345 0.0029 1.0000
9.250 1.1493 0.01719 0.01091 -0.0316 0.0027 1.0000
9.500 1.1609 0.01774 0.01151 -0.0289 0.0027 1.0000
9.750 1.1712 0.01839 0.01225 -0.0261 0.0027 1.0000
10.000 1.1834 0.01899 0.01290 -0.0238 0.0026 1.0000
10.250 1.1946 0.01967 0.01364 -0.0215 0.0025 1.0000
10.500 1.2046 0.02046 0.01450 -0.0191 0.0025 1.0000
10.750 1.2132 0.02138 0.01550 -0.0167 0.0024 1.0000
11.000 1.2223 0.02232 0.01651 -0.0145 0.0023 1.0000
11.250 1.2334 0.02317 0.01742 -0.0127 0.0021 1.0000
11.500 1.2380 0.02450 0.01885 -0.0103 0.0022 1.0000
11.750 1.2457 0.02570 0.02013 -0.0085 0.0021 1.0000
12.000 1.2511 0.02712 0.02163 -0.0066 0.0019 1.0000
12.250 1.2550 0.02873 0.02336 -0.0049 0.0020 1.0000
12.500 1.2643 0.02996 0.02466 -0.0037 0.0019 1.0000
12.750 1.2703 0.03154 0.02630 -0.0025 0.0017 1.0000
13.000 1.2724 0.03352 0.02838 -0.0012 0.0017 1.0000
13.250 1.2678 0.03623 0.03124 0.0002 0.0019 1.0000
13.500 1.2758 0.03783 0.03290 0.0008 0.0017 1.0000
13.750 1.2761 0.04025 0.03542 0.0015 0.0017 1.0000
14.000 1.2806 0.04231 0.03754 0.0018 0.0016 1.0000
14.250 1.2728 0.04576 0.04115 0.0024 0.0016 1.0000
14.500 1.2722 0.04855 0.04403 0.0025 0.0016 1.0000
14.750 1.2681 0.05186 0.04745 0.0025 0.0016 1.0000
15.000 1.2630 0.05541 0.05112 0.0022 0.0016 1.0000
15.250 1.2612 0.05870 0.05449 0.0016 0.0015 1.0000
15.500 1.2546 0.06268 0.05860 0.0009 0.0015 1.0000
15.750 1.2430 0.06752 0.06356 -0.0002 0.0015 1.0000
16.000 1.2351 0.07202 0.06819 -0.0014 0.0015 1.0000
16.250 1.2322 0.07595 0.07224 -0.0026 0.0015 1.0000
16.500 1.2203 0.08129 0.07771 -0.0043 0.0016 1.0000
16.750 1.2064 0.08718 0.08372 -0.0065 0.0015 1.0000
17.000 1.1966 0.09260 0.08925 -0.0086 0.0015 1.0000
17.250 1.1824 0.09884 0.09563 -0.0111 0.0015 1.0000
17.500 1.1746 0.10418 0.10107 -0.0134 0.0015 1.0000
17.750 1.1582 0.11116 0.10820 -0.0164 0.0016 1.0000
18.000 1.1411 0.11853 0.11567 -0.0199 0.0015 1.0000
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