MH 91 14.98% (mh91-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 91 14.98% (mh91-il) Reynolds number: 500,000 Max Cl/Cd: 78.06 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh91-il-500000.txt Download as CSV file: xf-mh91-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 91 14.98%
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.8641 0.03734 0.03354 -0.0234 1.0000 0.0158
-11.250 -0.9671 0.03842 0.03356 -0.0155 1.0000 0.0128
-11.000 -0.9660 0.03736 0.03234 -0.0124 1.0000 0.0127
-10.750 -0.9570 0.03491 0.02975 -0.0107 1.0000 0.0126
-10.500 -0.9464 0.03247 0.02718 -0.0092 1.0000 0.0124
-10.250 -0.9353 0.03037 0.02489 -0.0074 1.0000 0.0124
-10.000 -0.9210 0.02854 0.02289 -0.0060 1.0000 0.0124
-9.750 -0.9046 0.02685 0.02102 -0.0047 1.0000 0.0124
-9.500 -0.8858 0.02539 0.01944 -0.0037 1.0000 0.0124
-9.250 -0.8662 0.02411 0.01803 -0.0026 1.0000 0.0125
-9.000 -0.8456 0.02314 0.01692 -0.0017 1.0000 0.0126
-8.750 -0.8243 0.02147 0.01521 -0.0011 1.0000 0.0129
-8.500 -0.7931 0.02017 0.01389 -0.0025 0.9531 0.0132
-8.250 -0.7750 0.01948 0.01310 -0.0007 0.9175 0.0134
-8.000 -0.7595 0.01888 0.01240 0.0016 0.8932 0.0138
-7.750 -0.7418 0.01829 0.01171 0.0035 0.8733 0.0142
-7.500 -0.7232 0.01766 0.01098 0.0053 0.8560 0.0145
-7.250 -0.7033 0.01712 0.01033 0.0068 0.8401 0.0150
-7.000 -0.6827 0.01660 0.00970 0.0082 0.8253 0.0154
-6.750 -0.6641 0.01583 0.00886 0.0098 0.8109 0.0159
-6.500 -0.6430 0.01526 0.00825 0.0110 0.7968 0.0166
-6.250 -0.6204 0.01480 0.00772 0.0120 0.7834 0.0175
-6.000 -0.5970 0.01441 0.00723 0.0130 0.7706 0.0185
-5.750 -0.5750 0.01388 0.00665 0.0141 0.7576 0.0204
-5.500 -0.5511 0.01345 0.00618 0.0149 0.7446 0.0227
-5.250 -0.5270 0.01303 0.00572 0.0157 0.7322 0.0264
-5.000 -0.5036 0.01255 0.00522 0.0166 0.7202 0.0344
-4.750 -0.4812 0.01189 0.00471 0.0176 0.7076 0.0629
-4.500 -0.4602 0.01112 0.00425 0.0187 0.6958 0.1258
-4.250 -0.4397 0.01036 0.00385 0.0198 0.6841 0.2118
-4.000 -0.4178 0.00971 0.00355 0.0207 0.6719 0.2963
-3.750 -0.3946 0.00925 0.00332 0.0215 0.6602 0.3607
-3.500 -0.3706 0.00890 0.00312 0.0222 0.6485 0.4162
-3.250 -0.3463 0.00855 0.00296 0.0229 0.6364 0.4715
-3.000 -0.3218 0.00827 0.00283 0.0236 0.6247 0.5241
-2.750 -0.2970 0.00804 0.00271 0.0244 0.6130 0.5713
-2.500 -0.2716 0.00782 0.00262 0.0250 0.6010 0.6140
-2.250 -0.2463 0.00766 0.00257 0.0258 0.5892 0.6577
-2.000 -0.2200 0.00758 0.00253 0.0264 0.5773 0.6898
-1.750 -0.1927 0.00754 0.00251 0.0267 0.5652 0.7147
-1.500 -0.1653 0.00754 0.00249 0.0271 0.5533 0.7355
-1.000 -0.1101 0.00758 0.00249 0.0277 0.5290 0.7709
-0.750 -0.0823 0.00763 0.00250 0.0280 0.5171 0.7863
-0.500 -0.0546 0.00770 0.00252 0.0283 0.5051 0.7989
-0.250 -0.0266 0.00775 0.00255 0.0285 0.4929 0.8100
0.000 0.0013 0.00783 0.00256 0.0287 0.4812 0.8211
0.250 0.0291 0.00792 0.00262 0.0290 0.4694 0.8300
0.500 0.0569 0.00800 0.00264 0.0292 0.4577 0.8396
0.750 0.0848 0.00809 0.00271 0.0294 0.4464 0.8473
1.000 0.1122 0.00821 0.00274 0.0296 0.4351 0.8562
1.250 0.1400 0.00830 0.00282 0.0299 0.4239 0.8628
1.500 0.1674 0.00841 0.00289 0.0302 0.4134 0.8706
2.000 0.2219 0.00864 0.00305 0.0308 0.3926 0.8843
2.250 0.2484 0.00879 0.00313 0.0312 0.3834 0.8924
2.500 0.2752 0.00890 0.00324 0.0317 0.3737 0.8985
2.750 0.3015 0.00905 0.00335 0.0322 0.3649 0.9059
3.000 0.3279 0.00917 0.00344 0.0326 0.3560 0.9119
3.250 0.3546 0.00932 0.00356 0.0330 0.3482 0.9171
3.500 0.3808 0.00943 0.00366 0.0334 0.3401 0.9235
3.750 0.4069 0.00958 0.00376 0.0338 0.3324 0.9288
4.000 0.4342 0.00970 0.00388 0.0341 0.3246 0.9336
4.250 0.4594 0.00988 0.00400 0.0346 0.3175 0.9399
4.500 0.4869 0.00997 0.00411 0.0348 0.3108 0.9446
4.750 0.5157 0.01016 0.00425 0.0346 0.3037 0.9490
5.000 0.5426 0.01029 0.00439 0.0348 0.2972 0.9548
5.250 0.5723 0.01045 0.00453 0.0344 0.2902 0.9591
5.500 0.6054 0.01068 0.00473 0.0332 0.2837 0.9622
5.750 0.6386 0.01084 0.00490 0.0320 0.2770 0.9660
6.000 0.6677 0.01107 0.00508 0.0316 0.2704 0.9711
6.250 0.7055 0.01126 0.00530 0.0294 0.2642 0.9726
6.500 0.7429 0.01147 0.00550 0.0272 0.2575 0.9741
6.750 0.7787 0.01173 0.00573 0.0253 0.2509 0.9761
7.000 0.8133 0.01190 0.00593 0.0236 0.2447 0.9787
7.250 0.8428 0.01219 0.00616 0.0229 0.2384 0.9828
7.500 0.8798 0.01235 0.00637 0.0208 0.2322 0.9842
7.750 0.9153 0.01259 0.00660 0.0188 0.2259 0.9860
8.000 0.9494 0.01288 0.00688 0.0171 0.2202 0.9883
8.250 0.9833 0.01307 0.00712 0.0156 0.2146 0.9909
8.500 1.0152 0.01339 0.00741 0.0142 0.2088 0.9938
8.750 1.0501 0.01364 0.00770 0.0124 0.2037 0.9957
9.000 1.0842 0.01389 0.00797 0.0106 0.1981 0.9980
9.250 1.1147 0.01431 0.00835 0.0094 0.1924 1.0000
9.500 1.1307 0.01449 0.00861 0.0112 0.1889 1.0000
9.750 1.1448 0.01472 0.00887 0.0133 0.1846 1.0000
10.000 1.1561 0.01504 0.00919 0.0159 0.1807 1.0000
10.250 1.1665 0.01539 0.00955 0.0186 0.1769 1.0000
10.500 1.1807 0.01562 0.00985 0.0207 0.1732 1.0000
10.750 1.1947 0.01594 0.01019 0.0228 0.1688 1.0000
11.000 1.2068 0.01645 0.01065 0.0249 0.1643 1.0000
11.250 1.2250 0.01675 0.01104 0.0261 0.1605 1.0000
11.500 1.2415 0.01715 0.01148 0.0275 0.1559 1.0000
11.750 1.2533 0.01776 0.01206 0.0294 0.1513 1.0000
12.000 1.2668 0.01818 0.01255 0.0312 0.1474 1.0000
12.250 1.2778 0.01873 0.01314 0.0331 0.1430 1.0000
12.500 1.2848 0.01956 0.01397 0.0351 0.1387 1.0000
12.750 1.2967 0.02028 0.01475 0.0364 0.1346 1.0000
13.000 1.3073 0.02113 0.01565 0.0375 0.1298 1.0000
13.250 1.3123 0.02241 0.01692 0.0388 0.1255 1.0000
13.500 1.3238 0.02338 0.01798 0.0395 0.1213 1.0000
13.750 1.3313 0.02468 0.01931 0.0402 0.1169 1.0000
14.000 1.3330 0.02650 0.02113 0.0409 0.1127 1.0000
14.250 1.3429 0.02779 0.02251 0.0413 0.1088 1.0000
14.500 1.3465 0.02965 0.02440 0.0415 0.1052 1.0000
15.000 1.3503 0.03390 0.02877 0.0417 0.0989 1.0000
15.250 1.3519 0.03617 0.03110 0.0415 0.0958 1.0000
15.500 1.3483 0.03903 0.03400 0.0411 0.0932 1.0000
15.750 1.3427 0.04214 0.03716 0.0406 0.0906 1.0000
16.000 1.3445 0.04462 0.03975 0.0400 0.0884 1.0000
16.250 1.3413 0.04767 0.04287 0.0392 0.0859 1.0000
16.500 1.3343 0.05129 0.04653 0.0381 0.0836 1.0000
16.750 1.3244 0.05530 0.05058 0.0368 0.0816 1.0000
17.000 1.3211 0.05870 0.05408 0.0356 0.0796 1.0000
17.250 1.3176 0.06221 0.05770 0.0343 0.0779 1.0000
17.500 1.3110 0.06619 0.06174 0.0327 0.0756 1.0000
17.750 1.3011 0.07067 0.06628 0.0308 0.0738 1.0000
18.000 1.2921 0.07502 0.07066 0.0290 0.0723 1.0000
18.250 1.2861 0.07912 0.07486 0.0272 0.0707 1.0000
18.500 1.2805 0.08332 0.07916 0.0253 0.0690 1.0000
18.750 1.2727 0.08790 0.08383 0.0231 0.0669 1.0000
19.000 1.2639 0.09262 0.08858 0.0208 0.0652 1.0000
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Polar data table (+)
Polar graphs
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