MH 81 13% (mh81-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 81 13% (mh81-il) Reynolds number: 200,000 Max Cl/Cd: 60.09 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh81-il-200000-n5.txt Download as CSV file: xf-mh81-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 81 13%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4617 0.07761 0.07410 -0.0010 0.7406 0.0143
-8.250 -0.4664 0.07319 0.06965 -0.0041 0.7236 0.0141
-7.750 -0.4878 0.06159 0.05785 -0.0123 0.6974 0.0138
-7.500 -0.4950 0.05475 0.05078 -0.0150 0.6873 0.0134
-7.250 -0.5025 0.04699 0.04261 -0.0164 0.6782 0.0130
-7.000 -0.5090 0.03852 0.03341 -0.0163 0.6703 0.0123
-6.750 -0.5050 0.03192 0.02583 -0.0149 0.6604 0.0119
-6.500 -0.4871 0.02919 0.02261 -0.0140 0.6473 0.0119
-6.250 -0.4663 0.02715 0.02017 -0.0131 0.6343 0.0120
-6.000 -0.4439 0.02545 0.01811 -0.0123 0.6216 0.0121
-5.750 -0.4202 0.02397 0.01633 -0.0117 0.6084 0.0123
-5.500 -0.3956 0.02268 0.01477 -0.0110 0.5959 0.0125
-5.250 -0.3704 0.02153 0.01338 -0.0104 0.5839 0.0127
-5.000 -0.3448 0.02048 0.01211 -0.0098 0.5717 0.0131
-4.750 -0.3188 0.01953 0.01097 -0.0092 0.5600 0.0135
-4.500 -0.2928 0.01869 0.00993 -0.0086 0.5490 0.0140
-4.250 -0.2667 0.01792 0.00903 -0.0080 0.5376 0.0146
-4.000 -0.2405 0.01732 0.00836 -0.0076 0.5268 0.0152
-3.500 -0.1872 0.01638 0.00722 -0.0068 0.5057 0.0184
-3.250 -0.1603 0.01598 0.00670 -0.0064 0.4960 0.0206
-3.000 -0.1335 0.01552 0.00618 -0.0060 0.4859 0.0228
-2.750 -0.1064 0.01511 0.00567 -0.0056 0.4764 0.0263
-2.500 -0.0793 0.01474 0.00525 -0.0052 0.4669 0.0340
-2.250 -0.0526 0.01425 0.00485 -0.0049 0.4583 0.0545
-2.000 -0.0264 0.01375 0.00457 -0.0046 0.4498 0.1119
-1.750 0.0000 0.01334 0.00439 -0.0043 0.4413 0.1763
-1.500 0.0261 0.01294 0.00422 -0.0040 0.4328 0.2519
-1.250 0.0508 0.01238 0.00409 -0.0036 0.4248 0.3706
-1.000 0.0725 0.01164 0.00399 -0.0024 0.4174 0.5463
-0.750 0.0928 0.01104 0.00402 -0.0003 0.4109 0.7174
-0.500 0.1194 0.01091 0.00416 0.0012 0.4032 0.8414
-0.250 0.1516 0.01102 0.00418 0.0011 0.3959 0.8948
0.000 0.1846 0.01113 0.00419 0.0007 0.3878 0.9251
0.250 0.2212 0.01127 0.00416 -0.0007 0.3807 0.9450
0.500 0.2594 0.01138 0.00417 -0.0024 0.3735 0.9606
0.750 0.3030 0.01152 0.00415 -0.0053 0.3663 0.9746
1.000 0.3563 0.01162 0.00412 -0.0102 0.3584 0.9892
1.250 0.4059 0.01170 0.00405 -0.0146 0.3508 1.0000
1.500 0.4303 0.01183 0.00406 -0.0140 0.3461 1.0000
1.750 0.4549 0.01193 0.00412 -0.0133 0.3409 1.0000
2.000 0.4794 0.01207 0.00417 -0.0127 0.3358 1.0000
2.500 0.5284 0.01237 0.00433 -0.0114 0.3264 1.0000
2.750 0.5529 0.01252 0.00443 -0.0108 0.3216 1.0000
3.000 0.5773 0.01271 0.00454 -0.0102 0.3175 1.0000
3.250 0.6018 0.01291 0.00467 -0.0095 0.3139 1.0000
3.500 0.6266 0.01308 0.00483 -0.0089 0.3095 1.0000
3.750 0.6513 0.01327 0.00499 -0.0084 0.3052 1.0000
4.000 0.6758 0.01349 0.00514 -0.0078 0.3014 1.0000
4.250 0.7004 0.01372 0.00533 -0.0072 0.2979 1.0000
4.500 0.7254 0.01393 0.00555 -0.0067 0.2942 1.0000
4.750 0.7502 0.01415 0.00576 -0.0062 0.2905 1.0000
5.000 0.7749 0.01439 0.00597 -0.0056 0.2869 1.0000
5.250 0.7995 0.01468 0.00618 -0.0051 0.2837 1.0000
5.500 0.8247 0.01491 0.00646 -0.0047 0.2802 1.0000
5.750 0.8499 0.01517 0.00674 -0.0043 0.2769 1.0000
6.000 0.8750 0.01543 0.00702 -0.0039 0.2735 1.0000
6.250 0.9000 0.01573 0.00727 -0.0035 0.2704 1.0000
6.500 0.9249 0.01605 0.00757 -0.0032 0.2674 1.0000
6.750 0.9502 0.01633 0.00794 -0.0029 0.2641 1.0000
7.000 0.9754 0.01663 0.00829 -0.0026 0.2610 1.0000
7.250 1.0004 0.01694 0.00861 -0.0023 0.2578 1.0000
7.500 1.0252 0.01728 0.00894 -0.0020 0.2548 1.0000
7.750 1.0499 0.01765 0.00932 -0.0017 0.2520 1.0000
8.000 1.0747 0.01799 0.00977 -0.0014 0.2490 1.0000
8.250 1.0993 0.01835 0.01020 -0.0011 0.2459 1.0000
8.500 1.1236 0.01871 0.01060 -0.0008 0.2429 1.0000
8.750 1.1477 0.01910 0.01099 -0.0005 0.2400 1.0000
9.000 1.1715 0.01953 0.01145 -0.0002 0.2373 1.0000
9.250 1.1951 0.01995 0.01200 0.0001 0.2344 1.0000
9.500 1.2185 0.02038 0.01253 0.0004 0.2312 1.0000
9.750 1.2414 0.02080 0.01302 0.0008 0.2282 1.0000
10.000 1.2640 0.02125 0.01348 0.0011 0.2254 1.0000
10.250 1.2862 0.02176 0.01404 0.0015 0.2228 1.0000
10.500 1.3076 0.02228 0.01472 0.0020 0.2197 1.0000
10.750 1.3285 0.02280 0.01536 0.0024 0.2164 1.0000
11.000 1.3487 0.02332 0.01595 0.0030 0.2133 1.0000
11.250 1.3685 0.02387 0.01651 0.0036 0.2106 1.0000
11.500 1.3869 0.02450 0.01726 0.0042 0.2077 1.0000
11.750 1.4038 0.02518 0.01811 0.0049 0.2043 1.0000
12.000 1.4194 0.02587 0.01891 0.0058 0.2010 1.0000
12.250 1.4335 0.02656 0.01965 0.0067 0.1981 1.0000
12.500 1.4447 0.02733 0.02044 0.0081 0.1955 1.0000
12.750 1.4507 0.02841 0.02172 0.0095 0.1924 1.0000
13.000 1.4567 0.02963 0.02308 0.0104 0.1891 1.0000
13.250 1.4628 0.03095 0.02449 0.0110 0.1861 1.0000
13.500 1.4693 0.03234 0.02590 0.0115 0.1833 1.0000
13.750 1.4728 0.03416 0.02787 0.0116 0.1804 1.0000
14.000 1.4739 0.03631 0.03018 0.0115 0.1770 1.0000
14.250 1.4747 0.03857 0.03255 0.0112 0.1737 1.0000
14.500 1.4766 0.04076 0.03479 0.0108 0.1708 1.0000
14.750 1.4744 0.04353 0.03768 0.0102 0.1677 1.0000
15.000 1.4676 0.04699 0.04131 0.0091 0.1643 1.0000
15.250 1.4613 0.05042 0.04485 0.0079 0.1610 1.0000
15.500 1.4579 0.05352 0.04799 0.0069 0.1580 1.0000
15.750 1.4473 0.05768 0.05228 0.0054 0.1549 1.0000
16.000 1.4307 0.06285 0.05763 0.0032 0.1513 1.0000
16.250 1.4185 0.06757 0.06243 0.0011 0.1479 1.0000
16.500 1.4168 0.07083 0.06568 -0.0002 0.1448 1.0000
16.750 1.3895 0.07824 0.07330 -0.0037 0.1413 1.0000
17.000 1.3671 0.08510 0.08029 -0.0070 0.1375 1.0000
17.250 1.3629 0.08909 0.08430 -0.0089 0.1340 1.0000
17.500 1.3396 0.09638 0.09172 -0.0124 0.1304 1.0000
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Polar data table (+)
Polar graphs
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