MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 95 15.86% (mh95-il) Reynolds number: 50,000 Max Cl/Cd: 28.97 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh95-il-50000-n5.txt Download as CSV file: xf-mh95-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 95 15.86%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5310 0.10114 0.09300 -0.0575 1.0000 0.0512
-12.500 -0.5533 0.09388 0.08571 -0.0609 1.0000 0.0507
-12.250 -0.5834 0.08654 0.07831 -0.0641 1.0000 0.0503
-12.000 -0.6128 0.08055 0.07222 -0.0660 1.0000 0.0498
-11.750 -0.6423 0.07552 0.06705 -0.0664 1.0000 0.0496
-11.500 -0.6682 0.07148 0.06288 -0.0655 1.0000 0.0493
-11.250 -0.6923 0.06808 0.05934 -0.0635 1.0000 0.0492
-11.000 -0.7151 0.06517 0.05627 -0.0606 1.0000 0.0491
-10.750 -0.7363 0.06270 0.05364 -0.0569 1.0000 0.0491
-10.500 -0.7567 0.06058 0.05137 -0.0524 1.0000 0.0491
-10.250 -0.7743 0.05864 0.04927 -0.0476 1.0000 0.0492
-10.000 -0.7864 0.05653 0.04694 -0.0433 1.0000 0.0495
-9.750 -0.7953 0.05437 0.04454 -0.0393 1.0000 0.0501
-9.500 -0.8009 0.05228 0.04215 -0.0354 1.0000 0.0507
-9.250 -0.8033 0.05024 0.03977 -0.0317 1.0000 0.0515
-9.000 -0.7949 0.04865 0.03820 -0.0295 1.0000 0.0527
-8.750 -0.7871 0.04708 0.03653 -0.0270 1.0000 0.0540
-8.500 -0.7776 0.04548 0.03477 -0.0246 1.0000 0.0552
-8.250 -0.7656 0.04385 0.03293 -0.0224 1.0000 0.0566
-8.000 -0.7502 0.04229 0.03113 -0.0205 1.0000 0.0579
-7.750 -0.7328 0.04088 0.02963 -0.0189 1.0000 0.0594
-7.500 -0.7175 0.03971 0.02848 -0.0171 1.0000 0.0615
-7.250 -0.7026 0.03865 0.02733 -0.0151 1.0000 0.0645
-7.000 -0.6873 0.03762 0.02622 -0.0131 1.0000 0.0678
-6.750 -0.6749 0.03665 0.02528 -0.0108 1.0000 0.0712
-6.500 -0.6614 0.03574 0.02425 -0.0085 1.0000 0.0755
-6.250 -0.6513 0.03477 0.02334 -0.0060 1.0000 0.0800
-6.000 -0.6414 0.03388 0.02240 -0.0034 1.0000 0.0871
-5.750 -0.6332 0.03290 0.02147 -0.0007 1.0000 0.0957
-5.500 -0.6253 0.03190 0.02056 0.0021 1.0000 0.1080
-5.250 -0.6188 0.03072 0.01963 0.0049 1.0000 0.1297
-5.000 -0.6135 0.02943 0.01875 0.0077 1.0000 0.1725
-4.750 -0.6016 0.02792 0.01798 0.0090 0.9964 0.2716
-4.500 -0.5827 0.02676 0.01765 0.0094 0.9894 0.4011
-4.250 -0.5582 0.02662 0.01828 0.0107 0.9829 0.5242
-4.000 -0.5309 0.02749 0.01954 0.0128 0.9758 0.6193
-3.750 -0.5009 0.02855 0.02053 0.0139 0.9687 0.6803
-3.500 -0.4742 0.02932 0.02116 0.0153 0.9603 0.7152
-3.250 -0.4364 0.03025 0.02188 0.0147 0.9540 0.7388
-3.000 -0.4064 0.03076 0.02222 0.0151 0.9456 0.7586
-2.750 -0.3665 0.03139 0.02264 0.0136 0.9393 0.7772
-2.500 -0.3377 0.03172 0.02280 0.0138 0.9300 0.7940
-2.250 -0.2957 0.03217 0.02306 0.0117 0.9237 0.8101
-2.000 -0.2706 0.03230 0.02305 0.0123 0.9133 0.8259
-1.750 -0.2169 0.03276 0.02334 0.0081 0.9079 0.8368
-1.500 -0.1866 0.03284 0.02330 0.0076 0.8973 0.8491
-1.250 -0.1483 0.03288 0.02320 0.0056 0.8897 0.8620
-1.000 -0.1040 0.03300 0.02321 0.0026 0.8799 0.8705
-0.750 -0.0655 0.03294 0.02305 0.0005 0.8711 0.8813
-0.500 -0.0192 0.03290 0.02292 -0.0030 0.8614 0.8892
-0.250 0.0155 0.03274 0.02269 -0.0045 0.8505 0.8986
0.000 0.0715 0.03251 0.02238 -0.0098 0.8422 0.9043
0.250 0.0994 0.03229 0.02212 -0.0101 0.8292 0.9136
0.500 0.1560 0.03188 0.02166 -0.0153 0.8205 0.9181
0.750 0.1961 0.03149 0.02124 -0.0176 0.8083 0.9248
1.000 0.2327 0.03111 0.02085 -0.0192 0.7949 0.9312
1.250 0.2813 0.03054 0.02026 -0.0229 0.7832 0.9358
1.500 0.3271 0.02992 0.01964 -0.0258 0.7714 0.9411
2.000 0.4077 0.02895 0.01868 -0.0301 0.7395 0.9508
2.250 0.4429 0.02849 0.01823 -0.0313 0.7225 0.9564
2.500 0.4857 0.02796 0.01769 -0.0337 0.7042 0.9603
2.750 0.5272 0.02746 0.01718 -0.0360 0.6844 0.9646
3.000 0.5645 0.02706 0.01673 -0.0374 0.6638 0.9691
3.250 0.5991 0.02682 0.01649 -0.0387 0.6395 0.9737
3.500 0.6340 0.02659 0.01620 -0.0398 0.6144 0.9783
3.750 0.6669 0.02644 0.01596 -0.0407 0.5893 0.9829
4.000 0.6981 0.02641 0.01588 -0.0415 0.5617 0.9877
4.250 0.7281 0.02644 0.01579 -0.0420 0.5350 0.9927
4.500 0.7564 0.02657 0.01584 -0.0425 0.5069 0.9979
4.750 0.7754 0.02677 0.01592 -0.0411 0.4829 1.0000
5.000 0.7834 0.02707 0.01616 -0.0378 0.4612 1.0000
5.250 0.7907 0.02739 0.01640 -0.0344 0.4406 1.0000
5.500 0.7973 0.02772 0.01665 -0.0310 0.4213 1.0000
5.750 0.8030 0.02807 0.01693 -0.0274 0.4031 1.0000
6.000 0.8078 0.02843 0.01724 -0.0236 0.3862 1.0000
6.250 0.8115 0.02880 0.01754 -0.0198 0.3702 1.0000
6.500 0.8151 0.02918 0.01784 -0.0159 0.3557 1.0000
6.750 0.8176 0.02956 0.01815 -0.0119 0.3419 1.0000
7.000 0.8175 0.02995 0.01854 -0.0074 0.3286 1.0000
7.250 0.8173 0.03033 0.01888 -0.0030 0.3164 1.0000
7.500 0.8189 0.03072 0.01919 0.0012 0.3048 1.0000
7.750 0.8199 0.03119 0.01966 0.0052 0.2929 1.0000
8.000 0.8258 0.03176 0.02020 0.0084 0.2813 1.0000
8.250 0.8355 0.03237 0.02071 0.0109 0.2702 1.0000
8.500 0.8444 0.03311 0.02147 0.0134 0.2583 1.0000
8.750 0.8562 0.03392 0.02229 0.0153 0.2475 1.0000
9.000 0.8713 0.03470 0.02295 0.0167 0.2380 1.0000
9.250 0.8820 0.03570 0.02405 0.0186 0.2277 1.0000
9.500 0.8974 0.03659 0.02489 0.0198 0.2194 1.0000
9.750 0.9098 0.03770 0.02610 0.0213 0.2109 1.0000
10.000 0.9275 0.03865 0.02696 0.0221 0.2040 1.0000
10.250 0.9373 0.03996 0.02847 0.0237 0.1968 1.0000
10.500 0.9539 0.04098 0.02943 0.0246 0.1907 1.0000
10.750 0.9654 0.04240 0.03099 0.0258 0.1851 1.0000
11.000 0.9756 0.04388 0.03260 0.0271 0.1799 1.0000
11.250 0.9924 0.04503 0.03374 0.0278 0.1753 1.0000
11.500 1.0017 0.04667 0.03551 0.0290 0.1712 1.0000
11.750 1.0032 0.04870 0.03777 0.0307 0.1671 1.0000
12.000 1.0098 0.05045 0.03964 0.0318 0.1633 1.0000
12.250 1.0253 0.05184 0.04104 0.0324 0.1601 1.0000
12.500 1.0304 0.05396 0.04328 0.0334 0.1574 1.0000
12.750 1.0160 0.05729 0.04693 0.0349 0.1551 1.0000
13.000 0.9992 0.06102 0.05092 0.0360 0.1527 1.0000
13.250 0.9822 0.06510 0.05521 0.0364 0.1506 1.0000
13.500 0.9666 0.06934 0.05961 0.0362 0.1484 1.0000
13.750 0.9682 0.07206 0.06239 0.0361 0.1461 1.0000
14.000 0.9737 0.07463 0.06499 0.0359 0.1441 1.0000
14.250 0.7312 0.11805 0.10886 0.0137 0.1413 1.0000
14.500 0.7029 0.12843 0.11925 0.0084 0.1389 1.0000
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