MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 92 15.49% (mh92-il) Reynolds number: 200,000 Max Cl/Cd: 54.69 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh92-il-200000-n5.txt Download as CSV file: xf-mh92-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 92 15.49%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.7481 0.11152 0.10759 0.0094 1.0000 0.0124
-14.500 -0.7791 0.09915 0.09505 0.0013 1.0000 0.0122
-14.250 -0.8105 0.08788 0.08356 -0.0064 1.0000 0.0121
-14.000 -0.8319 0.07978 0.07528 -0.0118 1.0000 0.0119
-13.750 -0.8583 0.07165 0.06689 -0.0170 1.0000 0.0120
-13.500 -0.8751 0.06581 0.06084 -0.0201 1.0000 0.0119
-13.250 -0.8917 0.06049 0.05529 -0.0224 1.0000 0.0119
-13.000 -0.9062 0.05584 0.05040 -0.0237 1.0000 0.0120
-12.750 -0.9162 0.05203 0.04637 -0.0241 1.0000 0.0120
-12.500 -0.9235 0.04870 0.04281 -0.0239 1.0000 0.0120
-12.250 -0.9288 0.04566 0.03954 -0.0232 1.0000 0.0121
-12.000 -0.9303 0.04307 0.03673 -0.0223 1.0000 0.0122
-11.750 -0.9299 0.04067 0.03409 -0.0210 1.0000 0.0123
-11.500 -0.9257 0.03856 0.03178 -0.0196 1.0000 0.0124
-11.250 -0.9199 0.03661 0.02961 -0.0181 1.0000 0.0126
-11.000 -0.9103 0.03499 0.02791 -0.0169 1.0000 0.0127
-10.750 -0.8996 0.03351 0.02635 -0.0156 1.0000 0.0128
-10.500 -0.8883 0.03227 0.02506 -0.0142 1.0000 0.0131
-10.250 -0.8754 0.03102 0.02373 -0.0129 1.0000 0.0134
-10.000 -0.8618 0.02996 0.02260 -0.0115 1.0000 0.0138
-9.750 -0.8469 0.02884 0.02139 -0.0102 1.0000 0.0143
-9.500 -0.8310 0.02778 0.02022 -0.0089 1.0000 0.0148
-9.250 -0.8142 0.02668 0.01901 -0.0077 1.0000 0.0152
-9.000 -0.7984 0.02562 0.01795 -0.0064 1.0000 0.0156
-8.750 -0.7818 0.02471 0.01703 -0.0052 0.9788 0.0160
-8.500 -0.7554 0.02373 0.01597 -0.0057 0.9245 0.0166
-8.250 -0.7391 0.02302 0.01515 -0.0038 0.8936 0.0170
-8.000 -0.7246 0.02230 0.01431 -0.0016 0.8700 0.0176
-7.750 -0.7093 0.02162 0.01349 0.0006 0.8504 0.0182
-7.500 -0.6942 0.02093 0.01273 0.0027 0.8330 0.0189
-7.250 -0.6771 0.02033 0.01205 0.0045 0.8172 0.0197
-7.000 -0.6591 0.01973 0.01134 0.0062 0.8023 0.0210
-6.750 -0.6404 0.01917 0.01067 0.0078 0.7884 0.0222
-6.500 -0.6204 0.01866 0.01008 0.0092 0.7747 0.0244
-6.250 -0.5998 0.01813 0.00950 0.0105 0.7613 0.0274
-6.000 -0.5790 0.01761 0.00892 0.0117 0.7487 0.0314
-5.500 -0.5365 0.01655 0.00782 0.0141 0.7237 0.0484
-5.000 -0.4960 0.01527 0.00678 0.0166 0.7003 0.1099
-4.750 -0.4771 0.01447 0.00630 0.0179 0.6881 0.1760
-4.500 -0.4588 0.01370 0.00589 0.0193 0.6769 0.2542
-4.250 -0.4391 0.01311 0.00556 0.0206 0.6654 0.3248
-4.000 -0.4185 0.01262 0.00529 0.0219 0.6538 0.3846
-3.750 -0.3975 0.01221 0.00506 0.0233 0.6428 0.4410
-3.500 -0.3754 0.01186 0.00489 0.0245 0.6312 0.4946
-3.250 -0.3528 0.01156 0.00474 0.0257 0.6199 0.5455
-3.000 -0.3291 0.01135 0.00462 0.0268 0.6089 0.5887
-2.750 -0.3037 0.01120 0.00454 0.0275 0.5973 0.6206
-2.500 -0.2777 0.01111 0.00447 0.0282 0.5862 0.6482
-2.250 -0.2513 0.01106 0.00442 0.0289 0.5749 0.6741
-2.000 -0.2245 0.01105 0.00439 0.0294 0.5636 0.6980
-1.750 -0.1975 0.01107 0.00438 0.0300 0.5529 0.7188
-1.500 -0.1701 0.01110 0.00437 0.0304 0.5413 0.7366
-1.250 -0.1428 0.01115 0.00436 0.0308 0.5304 0.7523
-1.000 -0.1158 0.01121 0.00433 0.0313 0.5195 0.7668
-0.750 -0.0879 0.01128 0.00437 0.0316 0.5084 0.7790
-0.500 -0.0603 0.01137 0.00438 0.0319 0.4978 0.7902
-0.250 -0.0335 0.01144 0.00437 0.0323 0.4867 0.8022
0.000 -0.0052 0.01155 0.00443 0.0326 0.4763 0.8110
0.250 0.0215 0.01164 0.00443 0.0330 0.4660 0.8213
0.500 0.0497 0.01176 0.00451 0.0332 0.4551 0.8297
0.750 0.0762 0.01186 0.00454 0.0336 0.4454 0.8393
1.000 0.1043 0.01200 0.00463 0.0339 0.4349 0.8471
1.250 0.1304 0.01212 0.00468 0.0344 0.4254 0.8567
1.500 0.1588 0.01228 0.00479 0.0345 0.4156 0.8634
1.750 0.1846 0.01239 0.00486 0.0351 0.4064 0.8721
2.000 0.2128 0.01255 0.00495 0.0352 0.3970 0.8776
2.250 0.2409 0.01268 0.00506 0.0352 0.3879 0.8836
2.500 0.2653 0.01281 0.00510 0.0359 0.3797 0.8914
2.750 0.2952 0.01296 0.00524 0.0357 0.3707 0.8956
3.000 0.3233 0.01313 0.00535 0.0357 0.3625 0.9009
3.250 0.3481 0.01324 0.00545 0.0362 0.3547 0.9080
3.500 0.3776 0.01342 0.00558 0.0359 0.3467 0.9122
3.750 0.4073 0.01359 0.00573 0.0356 0.3388 0.9167
4.000 0.4334 0.01375 0.00586 0.0359 0.3316 0.9230
4.250 0.4618 0.01393 0.00602 0.0357 0.3250 0.9279
4.500 0.4933 0.01411 0.00620 0.0349 0.3173 0.9318
4.750 0.5218 0.01433 0.00636 0.0346 0.3108 0.9371
5.000 0.5490 0.01449 0.00655 0.0346 0.3041 0.9428
5.250 0.5821 0.01472 0.00676 0.0334 0.2976 0.9458
5.500 0.6136 0.01494 0.00698 0.0324 0.2914 0.9495
5.750 0.6415 0.01514 0.00719 0.0321 0.2847 0.9546
6.000 0.6714 0.01540 0.00741 0.0314 0.2789 0.9583
6.250 0.7052 0.01562 0.00769 0.0299 0.2730 0.9609
6.500 0.7372 0.01587 0.00795 0.0287 0.2667 0.9641
6.750 0.7659 0.01616 0.00820 0.0281 0.2612 0.9683
7.000 0.7971 0.01640 0.00852 0.0271 0.2553 0.9716
7.250 0.8303 0.01670 0.00882 0.0255 0.2494 0.9741
7.500 0.8615 0.01701 0.00915 0.0243 0.2441 0.9773
7.750 0.8908 0.01729 0.00950 0.0236 0.2383 0.9813
8.000 0.9220 0.01764 0.00984 0.0223 0.2329 0.9844
8.250 0.9539 0.01798 0.01024 0.0209 0.2274 0.9874
8.500 0.9841 0.01832 0.01064 0.0198 0.2215 0.9911
8.750 1.0133 0.01873 0.01104 0.0187 0.2162 0.9947
9.000 1.0446 0.01910 0.01150 0.0173 0.2103 0.9983
9.250 1.0654 0.01948 0.01192 0.0179 0.2052 1.0000
9.500 1.0751 0.01987 0.01231 0.0205 0.2015 1.0000
9.750 1.0856 0.02022 0.01273 0.0230 0.1975 1.0000
10.000 1.0956 0.02059 0.01317 0.0256 0.1935 1.0000
10.250 1.1044 0.02101 0.01361 0.0282 0.1894 1.0000
10.500 1.1122 0.02152 0.01409 0.0309 0.1861 1.0000
10.750 1.1238 0.02197 0.01464 0.0330 0.1821 1.0000
11.000 1.1331 0.02249 0.01523 0.0353 0.1780 1.0000
11.250 1.1390 0.02310 0.01585 0.0378 0.1745 1.0000
11.500 1.1458 0.02384 0.01661 0.0399 0.1710 1.0000
11.750 1.1560 0.02459 0.01747 0.0414 0.1668 1.0000
12.000 1.1645 0.02549 0.01842 0.0427 0.1628 1.0000
12.250 1.1713 0.02657 0.01952 0.0439 0.1592 1.0000
12.500 1.1803 0.02765 0.02069 0.0448 0.1554 1.0000
12.750 1.1886 0.02884 0.02197 0.0455 0.1513 1.0000
13.000 1.1944 0.03025 0.02344 0.0461 0.1476 1.0000
13.250 1.1992 0.03183 0.02504 0.0466 0.1442 1.0000
13.500 1.2062 0.03336 0.02670 0.0469 0.1402 1.0000
13.750 1.2098 0.03519 0.02860 0.0470 0.1362 1.0000
14.000 1.2113 0.03727 0.03070 0.0470 0.1330 1.0000
14.250 1.2147 0.03930 0.03285 0.0469 0.1296 1.0000
14.500 1.2164 0.04156 0.03521 0.0466 0.1259 1.0000
14.750 1.2154 0.04413 0.03784 0.0461 0.1226 1.0000
15.000 1.2128 0.04691 0.04064 0.0455 0.1196 1.0000
15.250 1.2124 0.04963 0.04350 0.0448 0.1162 1.0000
15.500 1.2094 0.05269 0.04665 0.0439 0.1131 1.0000
15.750 1.2048 0.05604 0.05005 0.0428 0.1103 1.0000
16.000 1.2000 0.05952 0.05358 0.0415 0.1075 1.0000
16.250 1.1955 0.06314 0.05734 0.0401 0.1044 1.0000
16.500 1.1892 0.06706 0.06135 0.0385 0.1016 1.0000
16.750 1.1828 0.07106 0.06539 0.0368 0.0991 1.0000
17.000 1.1772 0.07498 0.06936 0.0351 0.0968 1.0000
17.250 1.1691 0.07949 0.07401 0.0330 0.0941 1.0000
17.500 1.1610 0.08406 0.07868 0.0309 0.0915 1.0000
17.750 1.1534 0.08857 0.08323 0.0287 0.0891 1.0000
18.000 1.1485 0.09268 0.08735 0.0267 0.0869 1.0000
18.250 1.1374 0.09804 0.09286 0.0241 0.0845 1.0000
18.500 1.1274 0.10325 0.09819 0.0214 0.0822 1.0000
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Polar data table (+)
Polar graphs
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