MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 117 9.8% (mh117-il) Reynolds number: 500,000 Max Cl/Cd: 102.92 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh117-il-500000.txt Download as CSV file: xf-mh117-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 117 9.8%
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 -0.5145 0.06801 0.06583 -0.0403 1.0000 0.0084
-9.000 -0.5692 0.04767 0.04545 -0.0559 1.0000 0.0080
-8.750 -0.5941 0.04046 0.03792 -0.0598 1.0000 0.0080
-8.500 -0.6053 0.03621 0.03341 -0.0591 1.0000 0.0078
-8.250 -0.6153 0.03204 0.02889 -0.0570 1.0000 0.0075
-8.000 -0.6053 0.02680 0.02303 -0.0582 0.9976 0.0074
-7.750 -0.5747 0.02284 0.01851 -0.0613 0.9940 0.0074
-7.500 -0.5436 0.02050 0.01579 -0.0631 0.9898 0.0077
-7.250 -0.5099 0.01873 0.01373 -0.0651 0.9860 0.0081
-7.000 -0.4741 0.01739 0.01214 -0.0672 0.9832 0.0084
-6.750 -0.4425 0.01578 0.01031 -0.0685 0.9782 0.0087
-6.500 -0.4099 0.01414 0.00851 -0.0701 0.9734 0.0095
-6.250 -0.3733 0.01338 0.00769 -0.0722 0.9704 0.0105
-6.000 -0.3407 0.01278 0.00702 -0.0733 0.9641 0.0119
-5.750 -0.3077 0.01179 0.00588 -0.0744 0.9577 0.0133
-5.500 -0.2763 0.01098 0.00497 -0.0751 0.9496 0.0177
-5.250 -0.2447 0.01003 0.00414 -0.0759 0.9417 0.0471
-5.000 -0.2157 0.00969 0.00386 -0.0762 0.9307 0.0651
-4.750 -0.1869 0.00945 0.00362 -0.0763 0.9194 0.0797
-4.500 -0.1590 0.00924 0.00339 -0.0762 0.9078 0.0940
-4.250 -0.1317 0.00904 0.00316 -0.0760 0.8961 0.1093
-3.750 -0.0783 0.00861 0.00272 -0.0753 0.8723 0.1443
-3.500 -0.0515 0.00843 0.00255 -0.0750 0.8607 0.1667
-3.250 -0.0247 0.00823 0.00238 -0.0747 0.8497 0.1924
-3.000 0.0022 0.00807 0.00224 -0.0744 0.8392 0.2215
-2.750 0.0291 0.00790 0.00212 -0.0742 0.8287 0.2535
-2.500 0.0561 0.00774 0.00202 -0.0740 0.8181 0.2864
-2.250 0.0831 0.00759 0.00193 -0.0738 0.8081 0.3245
-2.000 0.1100 0.00745 0.00185 -0.0735 0.7987 0.3675
-1.750 0.1369 0.00728 0.00179 -0.0733 0.7883 0.4125
-1.500 0.1638 0.00711 0.00175 -0.0731 0.7785 0.4666
-1.250 0.1904 0.00696 0.00171 -0.0727 0.7690 0.5228
-1.000 0.2168 0.00678 0.00170 -0.0724 0.7588 0.5861
-0.750 0.2428 0.00660 0.00170 -0.0719 0.7487 0.6550
-0.500 0.2682 0.00644 0.00171 -0.0712 0.7392 0.7238
-0.250 0.2927 0.00629 0.00174 -0.0701 0.7296 0.7918
0.000 0.3160 0.00616 0.00178 -0.0688 0.7196 0.8582
0.250 0.3403 0.00609 0.00179 -0.0674 0.7103 0.9191
0.500 0.3774 0.00609 0.00176 -0.0691 0.7005 0.9674
0.750 0.4216 0.00609 0.00172 -0.0726 0.6895 0.9958
1.000 0.4507 0.00615 0.00172 -0.0728 0.6791 1.0000
1.250 0.4763 0.00624 0.00173 -0.0723 0.6689 1.0000
1.500 0.5021 0.00632 0.00175 -0.0718 0.6583 1.0000
1.750 0.5284 0.00640 0.00179 -0.0714 0.6470 1.0000
2.000 0.5547 0.00648 0.00184 -0.0710 0.6356 1.0000
2.250 0.5811 0.00658 0.00189 -0.0706 0.6241 1.0000
2.500 0.6075 0.00668 0.00195 -0.0703 0.6120 1.0000
2.750 0.6340 0.00679 0.00201 -0.0699 0.5992 1.0000
3.000 0.6604 0.00690 0.00209 -0.0696 0.5857 1.0000
3.250 0.6868 0.00701 0.00218 -0.0692 0.5704 1.0000
3.500 0.7131 0.00714 0.00227 -0.0689 0.5540 1.0000
3.750 0.7393 0.00729 0.00239 -0.0685 0.5355 1.0000
4.000 0.7650 0.00747 0.00250 -0.0680 0.5141 1.0000
4.250 0.7904 0.00768 0.00263 -0.0675 0.4891 1.0000
4.500 0.8154 0.00793 0.00279 -0.0670 0.4598 1.0000
4.750 0.8399 0.00824 0.00299 -0.0664 0.4245 1.0000
5.000 0.8637 0.00862 0.00322 -0.0657 0.3877 1.0000
5.250 0.8876 0.00902 0.00348 -0.0651 0.3527 1.0000
5.500 0.9109 0.00947 0.00378 -0.0644 0.3165 1.0000
5.750 0.9342 0.00994 0.00412 -0.0637 0.2814 1.0000
6.000 0.9576 0.01040 0.00445 -0.0630 0.2511 1.0000
6.500 1.0033 0.01140 0.00520 -0.0616 0.1923 1.0000
6.750 1.0261 0.01190 0.00560 -0.0609 0.1670 1.0000
7.000 1.0486 0.01242 0.00602 -0.0602 0.1430 1.0000
7.250 1.0707 0.01297 0.00649 -0.0594 0.1218 1.0000
7.500 1.0926 0.01352 0.00697 -0.0585 0.1030 1.0000
7.750 1.1139 0.01412 0.00750 -0.0576 0.0874 1.0000
8.000 1.1354 0.01468 0.00804 -0.0567 0.0760 1.0000
8.250 1.1568 0.01524 0.00860 -0.0558 0.0668 1.0000
8.500 1.1772 0.01586 0.00921 -0.0547 0.0585 1.0000
8.750 1.1974 0.01648 0.00982 -0.0537 0.0509 1.0000
9.000 1.2184 0.01699 0.01039 -0.0527 0.0452 1.0000
9.250 1.2361 0.01776 0.01113 -0.0513 0.0384 1.0000
9.500 1.2576 0.01817 0.01160 -0.0505 0.0343 1.0000
9.750 1.2741 0.01897 0.01237 -0.0490 0.0286 1.0000
10.000 1.2941 0.01944 0.01291 -0.0480 0.0252 1.0000
10.250 1.3076 0.02038 0.01383 -0.0461 0.0201 1.0000
10.500 1.3245 0.02095 0.01444 -0.0446 0.0164 1.0000
10.750 1.3341 0.02190 0.01543 -0.0420 0.0123 1.0000
11.000 1.3378 0.02325 0.01682 -0.0388 0.0089 1.0000
11.250 1.3486 0.02413 0.01776 -0.0367 0.0074 1.0000
11.500 1.3497 0.02573 0.01944 -0.0337 0.0063 1.0000
11.750 1.3538 0.02717 0.02102 -0.0313 0.0058 1.0000
12.000 1.3591 0.02859 0.02256 -0.0293 0.0053 1.0000
12.250 1.3625 0.03024 0.02432 -0.0274 0.0049 1.0000
12.500 1.3668 0.03189 0.02608 -0.0258 0.0046 1.0000
12.750 1.3688 0.03385 0.02815 -0.0244 0.0045 1.0000
13.000 1.3668 0.03629 0.03071 -0.0231 0.0042 1.0000
13.250 1.3542 0.03999 0.03458 -0.0220 0.0040 1.0000
13.500 1.3431 0.04380 0.03856 -0.0214 0.0039 1.0000
13.750 1.3370 0.04730 0.04219 -0.0214 0.0038 1.0000
14.000 1.3395 0.04995 0.04498 -0.0215 0.0037 1.0000
14.250 1.3317 0.05398 0.04919 -0.0221 0.0037 1.0000
14.500 1.3259 0.05797 0.05333 -0.0230 0.0036 1.0000
14.750 1.3176 0.06253 0.05806 -0.0243 0.0035 1.0000
15.000 1.3096 0.06727 0.06293 -0.0260 0.0035 1.0000
15.250 1.2983 0.07283 0.06866 -0.0282 0.0034 1.0000
15.500 1.2867 0.07872 0.07471 -0.0308 0.0034 1.0000
15.750 1.2747 0.08497 0.08112 -0.0338 0.0034 1.0000
16.000 1.2631 0.09149 0.08778 -0.0372 0.0033 1.0000
16.250 1.2489 0.09876 0.09520 -0.0410 0.0032 1.0000
16.500 1.2343 0.10631 0.10291 -0.0451 0.0033 1.0000
16.750 1.2195 0.11423 0.11098 -0.0495 0.0032 1.0000
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Polar data table (+)
Polar graphs
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