MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 30 7.84% (mh30-il) Reynolds number: 1,000,000 Max Cl/Cd: 84.49 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh30-il-1000000-n5.txt Download as CSV file: xf-mh30-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 30 7.84%
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4936 0.09564 0.09402 -0.0146 1.0000 0.0049
-9.250 -0.4881 0.09258 0.09097 -0.0161 1.0000 0.0060
-9.000 -0.4884 0.08829 0.08670 -0.0181 1.0000 0.0059
-8.750 -0.4869 0.08436 0.08279 -0.0200 1.0000 0.0062
-8.250 -0.4734 0.07813 0.07659 -0.0233 1.0000 0.0073
-6.250 -0.4356 0.02163 0.01827 -0.0538 0.9569 0.0032
-6.000 -0.4172 0.01839 0.01458 -0.0527 0.9466 0.0030
-5.750 -0.3962 0.01609 0.01191 -0.0515 0.9375 0.0029
-5.500 -0.3738 0.01427 0.00979 -0.0504 0.9291 0.0029
-5.250 -0.3499 0.01282 0.00807 -0.0496 0.9218 0.0028
-5.000 -0.3257 0.01165 0.00670 -0.0487 0.9150 0.0027
-4.750 -0.3008 0.01065 0.00553 -0.0481 0.9081 0.0027
-4.250 -0.2498 0.00925 0.00386 -0.0469 0.8940 0.0027
-4.000 -0.2237 0.00875 0.00323 -0.0464 0.8867 0.0027
-3.750 -0.1971 0.00836 0.00274 -0.0460 0.8784 0.0027
-3.500 -0.1703 0.00806 0.00233 -0.0456 0.8703 0.0027
-3.250 -0.1433 0.00783 0.00201 -0.0453 0.8616 0.0029
-3.000 -0.1160 0.00765 0.00173 -0.0451 0.8528 0.0030
-2.750 -0.0886 0.00751 0.00152 -0.0449 0.8439 0.0035
-2.250 -0.0346 0.00708 0.00118 -0.0445 0.8237 0.0402
-2.000 -0.0079 0.00679 0.00104 -0.0443 0.8125 0.0885
-1.750 0.0178 0.00633 0.00091 -0.0441 0.7991 0.1908
-1.500 0.0440 0.00606 0.00081 -0.0439 0.7823 0.2647
-1.000 0.0970 0.00575 0.00068 -0.0434 0.7420 0.3736
-0.750 0.1234 0.00563 0.00064 -0.0431 0.7192 0.4306
-0.500 0.1498 0.00554 0.00060 -0.0429 0.6937 0.4828
-0.250 0.1760 0.00550 0.00059 -0.0426 0.6660 0.5330
0.000 0.2022 0.00546 0.00060 -0.0423 0.6369 0.5840
0.250 0.2282 0.00544 0.00062 -0.0419 0.6076 0.6349
0.500 0.2541 0.00543 0.00065 -0.0416 0.5797 0.6854
0.750 0.2797 0.00542 0.00070 -0.0411 0.5513 0.7381
1.000 0.3050 0.00541 0.00075 -0.0406 0.5235 0.7897
1.250 0.3298 0.00542 0.00082 -0.0399 0.4941 0.8383
1.500 0.3539 0.00546 0.00089 -0.0390 0.4637 0.8873
1.750 0.3802 0.00553 0.00097 -0.0385 0.4336 0.9384
2.000 0.4189 0.00571 0.00105 -0.0410 0.3998 0.9733
2.250 0.4552 0.00592 0.00113 -0.0430 0.3661 0.9915
2.500 0.4876 0.00615 0.00123 -0.0442 0.3339 1.0000
2.750 0.5127 0.00637 0.00135 -0.0437 0.3052 1.0000
3.000 0.5379 0.00659 0.00147 -0.0432 0.2777 1.0000
3.250 0.5633 0.00682 0.00160 -0.0428 0.2524 1.0000
3.500 0.5885 0.00708 0.00175 -0.0424 0.2237 1.0000
3.750 0.6139 0.00734 0.00190 -0.0420 0.1987 1.0000
4.000 0.6396 0.00757 0.00208 -0.0416 0.1789 1.0000
4.250 0.6647 0.00788 0.00227 -0.0412 0.1516 1.0000
4.500 0.6894 0.00826 0.00250 -0.0408 0.1182 1.0000
4.750 0.7143 0.00862 0.00274 -0.0404 0.0924 1.0000
5.000 0.7382 0.00911 0.00304 -0.0398 0.0576 1.0000
5.250 0.7626 0.00956 0.00336 -0.0393 0.0339 1.0000
5.500 0.7877 0.00989 0.00364 -0.0389 0.0231 1.0000
6.000 0.8381 0.01054 0.00429 -0.0382 0.0113 1.0000
6.250 0.8628 0.01093 0.00465 -0.0377 0.0054 1.0000
6.500 0.8869 0.01143 0.00513 -0.0371 0.0016 1.0000
6.750 0.9117 0.01182 0.00557 -0.0366 0.0013 1.0000
7.000 0.9363 0.01222 0.00604 -0.0361 0.0012 1.0000
7.250 0.9607 0.01264 0.00653 -0.0356 0.0012 1.0000
7.500 0.9844 0.01317 0.00714 -0.0349 0.0011 1.0000
7.750 1.0078 0.01372 0.00777 -0.0343 0.0011 1.0000
8.000 1.0304 0.01438 0.00854 -0.0335 0.0011 1.0000
8.250 1.0525 0.01510 0.00940 -0.0326 0.0011 1.0000
8.500 1.0736 0.01591 0.01034 -0.0316 0.0010 1.0000
8.750 1.0941 0.01680 0.01136 -0.0306 0.0010 1.0000
9.000 1.1134 0.01780 0.01250 -0.0294 0.0010 1.0000
9.250 1.1314 0.01895 0.01381 -0.0280 0.0010 1.0000
9.500 1.1481 0.02022 0.01525 -0.0265 0.0010 1.0000
9.750 1.1632 0.02165 0.01687 -0.0248 0.0010 1.0000
10.000 1.1763 0.02327 0.01870 -0.0229 0.0010 1.0000
10.250 1.1871 0.02509 0.02074 -0.0208 0.0010 1.0000
10.500 1.1952 0.02705 0.02293 -0.0184 0.0010 1.0000
10.750 1.2008 0.02905 0.02516 -0.0159 0.0010 1.0000
11.000 1.1990 0.03126 0.02763 -0.0124 0.0010 1.0000
11.250 1.1915 0.03345 0.03003 -0.0084 0.0011 1.0000
11.500 1.1797 0.03613 0.03294 -0.0049 0.0011 1.0000
11.750 1.1651 0.03932 0.03634 -0.0023 0.0011 1.0000
12.000 1.1568 0.04216 0.03934 -0.0011 0.0011 1.0000
12.250 1.1432 0.04599 0.04336 -0.0008 0.0011 1.0000
12.500 1.1258 0.05096 0.04851 -0.0021 0.0011 1.0000
12.750 1.1105 0.05652 0.05424 -0.0048 0.0011 1.0000
13.000 1.0860 0.06490 0.06281 -0.0101 0.0011 1.0000
13.250 1.0697 0.07296 0.07100 -0.0157 0.0011 1.0000
13.500 1.0461 0.08359 0.08178 -0.0228 0.0011 1.0000
13.750 1.0341 0.09168 0.08995 -0.0278 0.0011 1.0000
14.000 1.0110 0.10274 0.10108 -0.0340 0.0011 1.0000
14.250 0.9852 0.11461 0.11302 -0.0402 0.0011 1.0000
14.500 0.9616 0.12615 0.12462 -0.0460 0.0011 1.0000
14.750 0.9352 0.13913 0.13764 -0.0523 0.0011 1.0000
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Polar data table (+)
Polar graphs
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