MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 78 14.47% (mh78-il) Reynolds number: 50,000 Max Cl/Cd: 18.4 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh78-il-50000-n5.txt Download as CSV file: xf-mh78-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 78 14.47%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5402 0.10038 0.09416 0.0159 1.0000 0.0490
-9.750 -0.5454 0.09401 0.08785 0.0119 1.0000 0.0485
-9.500 -0.5569 0.08597 0.07982 0.0058 1.0000 0.0478
-9.250 -0.5802 0.07789 0.07169 -0.0004 1.0000 0.0469
-9.000 -0.6084 0.07132 0.06498 -0.0037 1.0000 0.0460
-8.750 -0.6341 0.06615 0.05960 -0.0039 1.0000 0.0455
-8.500 -0.6451 0.06189 0.05513 -0.0036 1.0000 0.0456
-8.250 -0.6486 0.05809 0.05111 -0.0030 1.0000 0.0458
-8.000 -0.6464 0.05465 0.04743 -0.0023 1.0000 0.0465
-7.750 -0.6410 0.05128 0.04378 -0.0015 1.0000 0.0472
-7.500 -0.6323 0.04801 0.04017 -0.0007 1.0000 0.0480
-7.250 -0.6201 0.04482 0.03658 0.0001 1.0000 0.0489
-7.000 -0.6038 0.04180 0.03310 0.0006 1.0000 0.0498
-6.750 -0.5717 0.03949 0.03061 -0.0010 0.8922 0.0509
-6.500 -0.5497 0.03781 0.02862 0.0002 0.8394 0.0521
-6.250 -0.5313 0.03633 0.02677 0.0023 0.8019 0.0538
-6.000 -0.5115 0.03485 0.02482 0.0044 0.7707 0.0563
-5.750 -0.4917 0.03380 0.02367 0.0062 0.7439 0.0589
-5.500 -0.4685 0.03258 0.02216 0.0076 0.7188 0.0624
-5.250 -0.4449 0.03141 0.02087 0.0090 0.6959 0.0656
-5.000 -0.4204 0.03040 0.01962 0.0103 0.6747 0.0710
-4.750 -0.3965 0.02944 0.01862 0.0114 0.6547 0.0773
-4.250 -0.3469 0.02760 0.01659 0.0134 0.6183 0.0994
-4.000 -0.3229 0.02664 0.01570 0.0144 0.6020 0.1199
-3.750 -0.3001 0.02556 0.01485 0.0155 0.5871 0.1612
-3.500 -0.2786 0.02444 0.01417 0.0164 0.5714 0.2385
-3.250 -0.2597 0.02346 0.01369 0.0180 0.5575 0.3394
-3.000 -0.2440 0.02254 0.01338 0.0206 0.5460 0.4612
-2.750 -0.2139 0.02192 0.01374 0.0226 0.5304 0.6477
-2.500 -0.1567 0.02273 0.01462 0.0214 0.5128 0.7820
-2.250 -0.1226 0.02333 0.01489 0.0222 0.4999 0.8363
-2.000 -0.0839 0.02384 0.01504 0.0218 0.4867 0.8736
-1.750 -0.0383 0.02427 0.01515 0.0196 0.4724 0.9030
-1.500 0.0085 0.02455 0.01508 0.0170 0.4601 0.9283
-1.250 0.0603 0.02467 0.01486 0.0131 0.4474 0.9512
-1.000 0.1137 0.02473 0.01467 0.0085 0.4345 0.9729
-0.750 0.1685 0.02455 0.01412 0.0034 0.4240 0.9919
-0.500 0.2065 0.02452 0.01397 0.0008 0.4132 1.0000
-0.250 0.2276 0.02458 0.01377 0.0017 0.4069 1.0000
0.000 0.2509 0.02482 0.01396 0.0019 0.3987 1.0000
0.250 0.2733 0.02500 0.01399 0.0025 0.3917 1.0000
0.500 0.2951 0.02516 0.01391 0.0034 0.3862 1.0000
0.750 0.3187 0.02556 0.01434 0.0036 0.3781 1.0000
1.000 0.3410 0.02584 0.01448 0.0043 0.3722 1.0000
1.250 0.3628 0.02607 0.01450 0.0052 0.3677 1.0000
1.500 0.3861 0.02669 0.01520 0.0053 0.3603 1.0000
1.750 0.4083 0.02709 0.01552 0.0060 0.3546 1.0000
2.000 0.4300 0.02738 0.01563 0.0070 0.3503 1.0000
2.250 0.4524 0.02811 0.01641 0.0072 0.3444 1.0000
2.500 0.4742 0.02878 0.01709 0.0077 0.3387 1.0000
2.750 0.4957 0.02922 0.01744 0.0086 0.3344 1.0000
3.000 0.5171 0.02954 0.01758 0.0097 0.3309 1.0000
3.250 0.5374 0.03078 0.01903 0.0097 0.3246 1.0000
3.500 0.5575 0.03161 0.01987 0.0103 0.3198 1.0000
3.750 0.5780 0.03217 0.02036 0.0113 0.3161 1.0000
4.000 0.5990 0.03255 0.02059 0.0125 0.3131 1.0000
4.250 0.6148 0.03432 0.02263 0.0125 0.3072 1.0000
4.500 0.6316 0.03552 0.02391 0.0132 0.3026 1.0000
4.750 0.6500 0.03630 0.02466 0.0142 0.2991 1.0000
5.000 0.6697 0.03682 0.02508 0.0155 0.2965 1.0000
5.250 0.6800 0.03891 0.02737 0.0160 0.2919 1.0000
5.500 0.6862 0.04129 0.02994 0.0164 0.2868 1.0000
5.750 0.6981 0.04266 0.03134 0.0175 0.2832 1.0000
6.000 0.7143 0.04347 0.03211 0.0189 0.2805 1.0000
6.250 0.7338 0.04396 0.03251 0.0203 0.2785 1.0000
6.500 0.6723 0.05318 0.04224 0.0191 0.2704 1.0000
6.750 0.6581 0.05690 0.04598 0.0194 0.2661 1.0000
7.000 0.6715 0.05778 0.04681 0.0209 0.2637 1.0000
7.250 0.6928 0.05792 0.04690 0.0226 0.2620 1.0000
7.750 0.5705 0.07772 0.06676 0.0149 0.2484 1.0000
8.000 0.5880 0.07858 0.06758 0.0160 0.2463 1.0000
8.250 0.5651 0.08472 0.07372 0.0135 0.2423 1.0000
8.500 0.5495 0.08994 0.07895 0.0115 0.2387 1.0000
8.750 0.5504 0.09311 0.08212 0.0108 0.2355 1.0000
9.000 0.5606 0.09519 0.08418 0.0108 0.2328 1.0000
9.250 0.5764 0.09663 0.08562 0.0114 0.2307 1.0000
9.500 0.5795 0.09988 0.08886 0.0107 0.2287 1.0000
9.750 0.5616 0.10563 0.09465 0.0079 0.2255 1.0000
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Polar data table (+)
Polar graphs
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