MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 30 7.84% (mh30-il) Reynolds number: 200,000 Max Cl/Cd: 67.05 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh30-il-200000.txt Download as CSV file: xf-mh30-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4858 0.08492 0.08161 -0.0311 1.0000 0.0371
-8.000 -0.4888 0.08004 0.07673 -0.0359 1.0000 0.0371
-7.750 -0.4985 0.07292 0.06967 -0.0377 1.0000 0.0381
-7.500 -0.4933 0.07039 0.06719 -0.0356 1.0000 0.0391
-7.250 -0.4891 0.06717 0.06397 -0.0361 1.0000 0.0401
-7.000 -0.4851 0.06361 0.06039 -0.0374 1.0000 0.0412
-6.750 -0.4818 0.05976 0.05650 -0.0386 1.0000 0.0426
-6.500 -0.4785 0.05584 0.05243 -0.0395 1.0000 0.0444
-6.250 -0.4747 0.05175 0.04816 -0.0400 1.0000 0.0472
-6.000 -0.4776 0.04703 0.04289 -0.0399 1.0000 0.0510
-5.750 -0.4688 0.04380 0.03973 -0.0384 1.0000 0.0525
-5.500 -0.4590 0.04149 0.03740 -0.0368 1.0000 0.0546
-5.250 -0.4482 0.03892 0.03463 -0.0353 1.0000 0.0581
-5.000 -0.4379 0.03569 0.03099 -0.0341 1.0000 0.0653
-4.750 -0.4128 0.02777 0.02184 -0.0304 1.0000 0.0259
-4.500 -0.3953 0.02394 0.01773 -0.0291 1.0000 0.0225
-4.250 -0.3745 0.02121 0.01455 -0.0276 1.0000 0.0207
-4.000 -0.3517 0.01898 0.01190 -0.0262 1.0000 0.0196
-3.750 -0.3287 0.01732 0.00999 -0.0249 1.0000 0.0193
-3.500 -0.3058 0.01603 0.00856 -0.0237 1.0000 0.0198
-3.250 -0.2834 0.01499 0.00743 -0.0225 1.0000 0.0214
-3.000 -0.2612 0.01419 0.00652 -0.0215 1.0000 0.0237
-2.750 -0.2332 0.01246 0.00511 -0.0216 0.9986 0.0935
-2.500 -0.1984 0.01119 0.00487 -0.0241 0.9944 0.3314
-2.250 -0.1651 0.01049 0.00486 -0.0256 0.9888 0.5147
-2.000 -0.1342 0.00987 0.00504 -0.0259 0.9832 0.7213
-1.750 -0.0999 0.00958 0.00514 -0.0261 0.9785 0.8753
-1.500 -0.0228 0.00951 0.00494 -0.0360 0.9814 1.0000
-1.250 0.0168 0.00954 0.00478 -0.0387 0.9738 1.0000
-1.000 0.0640 0.00960 0.00468 -0.0429 0.9690 1.0000
-0.750 0.1031 0.00960 0.00457 -0.0453 0.9610 1.0000
-0.500 0.1516 0.00956 0.00443 -0.0496 0.9563 1.0000
-0.250 0.1936 0.00950 0.00429 -0.0525 0.9486 1.0000
0.000 0.2413 0.00935 0.00410 -0.0564 0.9428 1.0000
0.250 0.2775 0.00922 0.00395 -0.0579 0.9322 1.0000
0.500 0.3112 0.00909 0.00380 -0.0587 0.9212 1.0000
0.750 0.3410 0.00898 0.00366 -0.0586 0.9091 1.0000
1.000 0.3673 0.00889 0.00354 -0.0578 0.8956 1.0000
1.250 0.3916 0.00880 0.00344 -0.0565 0.8807 1.0000
1.500 0.4152 0.00873 0.00336 -0.0551 0.8649 1.0000
1.750 0.4389 0.00865 0.00326 -0.0536 0.8482 1.0000
2.000 0.4618 0.00863 0.00321 -0.0521 0.8281 1.0000
2.250 0.4857 0.00859 0.00314 -0.0507 0.8076 1.0000
2.500 0.5094 0.00860 0.00312 -0.0494 0.7826 1.0000
2.750 0.5333 0.00863 0.00315 -0.0481 0.7551 1.0000
3.000 0.5573 0.00872 0.00317 -0.0469 0.7236 1.0000
3.250 0.5812 0.00886 0.00321 -0.0457 0.6880 1.0000
3.500 0.6048 0.00908 0.00330 -0.0445 0.6486 1.0000
3.750 0.6280 0.00937 0.00344 -0.0433 0.6064 1.0000
4.000 0.6511 0.00971 0.00368 -0.0422 0.5610 1.0000
4.250 0.6738 0.01010 0.00391 -0.0411 0.5137 1.0000
4.500 0.6962 0.01053 0.00418 -0.0400 0.4637 1.0000
4.750 0.7183 0.01103 0.00450 -0.0390 0.4122 1.0000
5.000 0.7403 0.01158 0.00486 -0.0380 0.3613 1.0000
5.250 0.7623 0.01216 0.00527 -0.0370 0.3120 1.0000
5.500 0.7841 0.01279 0.00574 -0.0361 0.2626 1.0000
5.750 0.8056 0.01350 0.00633 -0.0353 0.2151 1.0000
6.000 0.8272 0.01423 0.00689 -0.0344 0.1677 1.0000
6.250 0.8479 0.01512 0.00755 -0.0335 0.1232 1.0000
6.500 0.8673 0.01626 0.00848 -0.0324 0.0841 1.0000
6.750 0.8850 0.01773 0.00985 -0.0307 0.0578 1.0000
7.000 0.9035 0.01915 0.01132 -0.0292 0.0444 1.0000
7.250 0.9223 0.02049 0.01270 -0.0278 0.0332 1.0000
7.500 0.9416 0.02169 0.01398 -0.0267 0.0200 1.0000
7.750 0.9573 0.02373 0.01610 -0.0249 0.0158 1.0000
8.000 0.9729 0.02696 0.01959 -0.0229 0.0140 1.0000
8.250 0.9912 0.02942 0.02237 -0.0214 0.0134 1.0000
8.500 1.0070 0.03238 0.02571 -0.0196 0.0131 1.0000
8.750 1.0187 0.03572 0.02947 -0.0176 0.0131 1.0000
9.000 1.0253 0.03943 0.03363 -0.0153 0.0132 1.0000
9.250 1.0265 0.04335 0.03807 -0.0128 0.0134 1.0000
9.500 1.0217 0.04746 0.04256 -0.0102 0.0137 1.0000
9.750 1.0112 0.05149 0.04691 -0.0075 0.0139 1.0000
10.000 0.9950 0.05501 0.05067 -0.0045 0.0140 1.0000
10.250 0.9758 0.05894 0.05480 -0.0027 0.0142 1.0000
10.500 0.9565 0.06329 0.05933 -0.0025 0.0143 1.0000
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Polar data table (+)
Polar graphs
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