MH 92 15.49% (mh92-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 92 15.49% (mh92-il) Reynolds number: 100,000 Max Cl/Cd: 39.98 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh92-il-100000-n5.txt Download as CSV file: xf-mh92-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6826 0.09644 0.09127 -0.0050 1.0000 0.0232
-12.750 -0.7488 0.07978 0.07421 -0.0173 1.0000 0.0224
-12.500 -0.7990 0.06983 0.06377 -0.0233 1.0000 0.0219
-12.250 -0.8231 0.06445 0.05810 -0.0250 1.0000 0.0218
-11.750 -0.8515 0.05683 0.04998 -0.0249 1.0000 0.0218
-11.500 -0.8588 0.05381 0.04676 -0.0239 1.0000 0.0218
-11.250 -0.8631 0.05104 0.04378 -0.0226 1.0000 0.0219
-11.000 -0.8642 0.04856 0.04111 -0.0210 1.0000 0.0220
-10.750 -0.8619 0.04630 0.03868 -0.0193 1.0000 0.0222
-10.500 -0.8570 0.04415 0.03637 -0.0176 1.0000 0.0224
-10.250 -0.8492 0.04217 0.03422 -0.0160 1.0000 0.0227
-10.000 -0.8390 0.04020 0.03207 -0.0144 1.0000 0.0230
-9.750 -0.8258 0.03832 0.03002 -0.0131 1.0000 0.0234
-9.500 -0.8095 0.03650 0.02802 -0.0121 1.0000 0.0238
-9.250 -0.7910 0.03475 0.02610 -0.0112 1.0000 0.0244
-9.000 -0.7707 0.03308 0.02424 -0.0104 1.0000 0.0251
-8.750 -0.7507 0.03162 0.02273 -0.0097 1.0000 0.0259
-8.500 -0.7325 0.03047 0.02161 -0.0089 1.0000 0.0271
-8.250 -0.7129 0.02935 0.02043 -0.0081 1.0000 0.0285
-8.000 -0.6937 0.02819 0.01922 -0.0073 1.0000 0.0301
-7.750 -0.6762 0.02716 0.01824 -0.0063 1.0000 0.0317
-7.500 -0.6541 0.02610 0.01712 -0.0061 0.9729 0.0336
-7.250 -0.6245 0.02495 0.01593 -0.0073 0.9389 0.0358
-7.000 -0.6007 0.02406 0.01494 -0.0070 0.9124 0.0402
-6.750 -0.5830 0.02330 0.01412 -0.0055 0.8889 0.0442
-6.500 -0.5674 0.02255 0.01331 -0.0034 0.8685 0.0493
-6.250 -0.5520 0.02181 0.01253 -0.0012 0.8505 0.0581
-6.000 -0.5368 0.02099 0.01175 0.0010 0.8339 0.0726
-5.750 -0.5220 0.02005 0.01100 0.0032 0.8185 0.1039
-5.500 -0.5089 0.01896 0.01031 0.0055 0.8041 0.1716
-5.000 -0.4806 0.01726 0.00942 0.0099 0.7764 0.3407
-4.750 -0.4638 0.01671 0.00914 0.0121 0.7629 0.4089
-4.500 -0.4456 0.01629 0.00894 0.0142 0.7505 0.4700
-4.250 -0.4257 0.01599 0.00879 0.0162 0.7380 0.5248
-4.000 -0.4039 0.01579 0.00871 0.0179 0.7248 0.5739
-3.750 -0.3799 0.01569 0.00868 0.0194 0.7127 0.6135
-3.500 -0.3549 0.01566 0.00860 0.0207 0.7007 0.6448
-3.250 -0.3278 0.01569 0.00861 0.0215 0.6875 0.6705
-3.000 -0.3018 0.01573 0.00857 0.0225 0.6755 0.6945
-2.750 -0.2750 0.01582 0.00854 0.0235 0.6638 0.7155
-2.500 -0.2472 0.01593 0.00857 0.0241 0.6506 0.7342
-2.250 -0.2202 0.01602 0.00855 0.0249 0.6387 0.7511
-2.000 -0.1942 0.01611 0.00848 0.0258 0.6272 0.7669
-1.750 -0.1647 0.01626 0.00854 0.0261 0.6142 0.7795
-1.500 -0.1362 0.01640 0.00855 0.0266 0.6023 0.7915
-1.250 -0.1101 0.01648 0.00850 0.0274 0.5911 0.8044
-1.000 -0.0811 0.01663 0.00855 0.0276 0.5784 0.8152
-0.750 -0.0521 0.01677 0.00857 0.0279 0.5667 0.8251
-0.500 -0.0282 0.01684 0.00851 0.0290 0.5558 0.8376
-0.250 0.0062 0.01704 0.00863 0.0283 0.5430 0.8445
0.000 0.0304 0.01713 0.00860 0.0292 0.5323 0.8562
0.250 0.0655 0.01732 0.00868 0.0283 0.5203 0.8626
0.500 0.0897 0.01741 0.00870 0.0292 0.5090 0.8739
0.750 0.1262 0.01759 0.00876 0.0279 0.4977 0.8793
1.000 0.1550 0.01771 0.00879 0.0279 0.4863 0.8879
1.250 0.1863 0.01783 0.00884 0.0274 0.4752 0.8947
1.500 0.2203 0.01796 0.00884 0.0263 0.4647 0.9005
1.750 0.2446 0.01804 0.00890 0.0269 0.4538 0.9095
2.000 0.2820 0.01818 0.00895 0.0251 0.4432 0.9135
2.250 0.3155 0.01830 0.00899 0.0240 0.4327 0.9192
2.500 0.3419 0.01842 0.00907 0.0242 0.4230 0.9268
2.750 0.3795 0.01854 0.00908 0.0222 0.4133 0.9305
3.000 0.4129 0.01868 0.00923 0.0209 0.4029 0.9359
3.250 0.4402 0.01882 0.00927 0.0208 0.3949 0.9427
3.500 0.4771 0.01896 0.00942 0.0188 0.3845 0.9466
3.750 0.5096 0.01913 0.00952 0.0177 0.3763 0.9519
4.000 0.5390 0.01930 0.00970 0.0170 0.3674 0.9578
4.250 0.5745 0.01946 0.00981 0.0152 0.3595 0.9618
4.500 0.6062 0.01965 0.01004 0.0141 0.3507 0.9671
4.750 0.6374 0.01985 0.01016 0.0131 0.3439 0.9719
5.000 0.6715 0.02006 0.01044 0.0114 0.3353 0.9761
5.250 0.7022 0.02028 0.01061 0.0104 0.3286 0.9811
5.500 0.7349 0.02053 0.01093 0.0089 0.3207 0.9851
5.750 0.7675 0.02077 0.01117 0.0075 0.3138 0.9893
6.000 0.7985 0.02107 0.01150 0.0063 0.3072 0.9937
6.250 0.8309 0.02135 0.01183 0.0048 0.2999 0.9976
6.500 0.8575 0.02165 0.01207 0.0045 0.2946 1.0000
6.750 0.8750 0.02204 0.01259 0.0058 0.2885 1.0000
7.000 0.8922 0.02240 0.01298 0.0072 0.2831 1.0000
7.250 0.9095 0.02275 0.01329 0.0086 0.2786 1.0000
7.500 0.9250 0.02320 0.01387 0.0102 0.2729 1.0000
7.750 0.9405 0.02361 0.01434 0.0119 0.2678 1.0000
8.000 0.9563 0.02400 0.01471 0.0136 0.2634 1.0000
8.250 0.9700 0.02450 0.01530 0.0154 0.2585 1.0000
8.500 0.9831 0.02498 0.01588 0.0174 0.2532 1.0000
8.750 0.9968 0.02541 0.01631 0.0194 0.2489 1.0000
9.000 1.0100 0.02590 0.01683 0.0214 0.2447 1.0000
9.250 1.0202 0.02649 0.01756 0.0237 0.2395 1.0000
9.500 1.0321 0.02698 0.01809 0.0258 0.2348 1.0000
9.750 1.0464 0.02743 0.01848 0.0276 0.2309 1.0000
10.000 1.0540 0.02816 0.01939 0.0300 0.2259 1.0000
10.250 1.0640 0.02879 0.02009 0.0321 0.2211 1.0000
10.500 1.0768 0.02931 0.02060 0.0338 0.2170 1.0000
10.750 1.0856 0.03010 0.02149 0.0358 0.2126 1.0000
11.000 1.0923 0.03096 0.02249 0.0378 0.2078 1.0000
11.250 1.1001 0.03167 0.02323 0.0399 0.2038 1.0000
11.500 1.1096 0.03238 0.02391 0.0416 0.2001 1.0000
11.750 1.1080 0.03372 0.02545 0.0437 0.1959 1.0000
12.000 1.1112 0.03496 0.02679 0.0451 0.1917 1.0000
12.250 1.1193 0.03598 0.02783 0.0462 0.1879 1.0000
12.500 1.1227 0.03746 0.02939 0.0471 0.1841 1.0000
12.750 1.1191 0.03957 0.03168 0.0477 0.1799 1.0000
13.000 1.1211 0.04134 0.03352 0.0481 0.1760 1.0000
13.250 1.1311 0.04250 0.03466 0.0485 0.1724 1.0000
13.500 1.1215 0.04557 0.03794 0.0483 0.1687 1.0000
13.750 1.1120 0.04882 0.04135 0.0478 0.1647 1.0000
14.000 1.1128 0.05110 0.04368 0.0474 0.1610 1.0000
14.250 1.1199 0.05276 0.04533 0.0473 0.1577 1.0000
14.500 1.0918 0.05869 0.05152 0.0451 0.1542 1.0000
14.750 1.0703 0.06419 0.05719 0.0428 0.1506 1.0000
15.000 1.0729 0.06664 0.05966 0.0420 0.1471 1.0000
15.250 1.0699 0.06994 0.06300 0.0408 0.1439 1.0000
15.500 0.9006 0.10071 0.09414 0.0247 0.1352 1.0000
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Polar data table (+)
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