MH 23 8% (mh23-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 23 8% (mh23-il) Reynolds number: 100,000 Max Cl/Cd: 45.95 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh23-il-100000-n5.txt Download as CSV file: xf-mh23-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 23 8%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4983 0.11030 0.10530 -0.0245 1.0000 0.0424
-9.750 -0.4998 0.10655 0.10162 -0.0274 1.0000 0.0426
-9.500 -0.5014 0.10256 0.09768 -0.0302 1.0000 0.0428
-9.250 -0.5033 0.09848 0.09365 -0.0331 1.0000 0.0428
-9.000 -0.5063 0.09426 0.08948 -0.0362 1.0000 0.0429
-8.500 -0.4921 0.08480 0.07993 -0.0304 1.0000 0.0248
-8.000 -0.4436 0.06426 0.05973 -0.0388 1.0000 0.0189
-7.500 -0.5302 0.06772 0.06297 -0.0347 1.0000 0.0190
-7.250 -0.5385 0.06441 0.05962 -0.0329 1.0000 0.0186
-7.000 -0.5439 0.06126 0.05639 -0.0309 1.0000 0.0183
-6.750 -0.5478 0.05800 0.05292 -0.0287 1.0000 0.0179
-6.500 -0.5499 0.05459 0.04937 -0.0264 1.0000 0.0176
-6.250 -0.5493 0.05126 0.04586 -0.0241 1.0000 0.0172
-6.000 -0.5467 0.04788 0.04225 -0.0216 1.0000 0.0168
-5.750 -0.5419 0.04451 0.03861 -0.0191 1.0000 0.0164
-5.500 -0.5348 0.04123 0.03503 -0.0165 1.0000 0.0160
-5.250 -0.5253 0.03814 0.03159 -0.0140 1.0000 0.0157
-5.000 -0.5137 0.03512 0.02817 -0.0115 1.0000 0.0153
-4.750 -0.4997 0.03232 0.02495 -0.0090 1.0000 0.0150
-4.500 -0.4834 0.02971 0.02189 -0.0067 1.0000 0.0148
-4.250 -0.4650 0.02739 0.01913 -0.0047 1.0000 0.0145
-4.000 -0.4447 0.02535 0.01668 -0.0028 1.0000 0.0144
-3.750 -0.4230 0.02350 0.01449 -0.0012 1.0000 0.0146
-3.500 -0.4011 0.02201 0.01274 0.0003 1.0000 0.0147
-3.250 -0.3794 0.02069 0.01124 0.0019 1.0000 0.0152
-3.000 -0.3587 0.01957 0.00996 0.0035 1.0000 0.0159
-2.750 -0.3375 0.01873 0.00895 0.0049 0.9997 0.0173
-2.500 -0.3067 0.01791 0.00789 0.0041 0.9960 0.0230
-2.250 -0.2754 0.01713 0.00701 0.0035 0.9922 0.0350
-2.000 -0.2070 0.01351 0.00725 -0.0031 1.0000 0.9380
-1.750 -0.1122 0.01395 0.00711 -0.0164 1.0000 1.0000
-1.500 -0.0995 0.01394 0.00692 -0.0140 1.0000 1.0000
-1.250 -0.0716 0.01400 0.00672 -0.0145 0.9967 1.0000
-1.000 -0.0342 0.01411 0.00663 -0.0170 0.9910 1.0000
-0.750 0.0037 0.01422 0.00658 -0.0195 0.9849 1.0000
-0.500 0.0423 0.01434 0.00656 -0.0222 0.9788 1.0000
-0.250 0.0807 0.01443 0.00651 -0.0248 0.9719 1.0000
0.000 0.1188 0.01450 0.00651 -0.0272 0.9647 1.0000
0.250 0.1595 0.01456 0.00653 -0.0301 0.9576 1.0000
0.500 0.1964 0.01458 0.00652 -0.0322 0.9488 1.0000
0.750 0.2430 0.01457 0.00653 -0.0362 0.9425 1.0000
1.250 0.3153 0.01443 0.00644 -0.0396 0.9211 1.0000
1.500 0.3503 0.01429 0.00637 -0.0409 0.9090 1.0000
1.750 0.3823 0.01412 0.00630 -0.0415 0.8951 1.0000
2.000 0.4115 0.01394 0.00619 -0.0414 0.8794 1.0000
2.250 0.4365 0.01376 0.00609 -0.0405 0.8600 1.0000
2.500 0.4613 0.01356 0.00597 -0.0394 0.8371 1.0000
2.750 0.4867 0.01335 0.00585 -0.0383 0.8093 1.0000
3.000 0.5170 0.01309 0.00573 -0.0380 0.7746 1.0000
3.250 0.5501 0.01284 0.00546 -0.0380 0.7269 1.0000
3.500 0.5791 0.01283 0.00530 -0.0374 0.6645 1.0000
3.750 0.6024 0.01311 0.00536 -0.0358 0.5956 1.0000
4.000 0.6223 0.01356 0.00556 -0.0339 0.5248 1.0000
4.250 0.6406 0.01412 0.00593 -0.0320 0.4563 1.0000
4.500 0.6582 0.01474 0.00631 -0.0300 0.3897 1.0000
4.750 0.6754 0.01542 0.00675 -0.0281 0.3259 1.0000
5.000 0.6925 0.01614 0.00726 -0.0262 0.2653 1.0000
5.250 0.7096 0.01692 0.00783 -0.0245 0.2092 1.0000
5.500 0.7266 0.01776 0.00847 -0.0227 0.1586 1.0000
5.750 0.7431 0.01871 0.00920 -0.0210 0.1133 1.0000
6.000 0.7596 0.01969 0.01010 -0.0191 0.0831 1.0000
6.250 0.7757 0.02075 0.01106 -0.0172 0.0594 1.0000
6.500 0.7909 0.02192 0.01228 -0.0150 0.0474 1.0000
6.750 0.8056 0.02317 0.01377 -0.0127 0.0403 1.0000
7.000 0.8198 0.02472 0.01549 -0.0102 0.0354 1.0000
7.250 0.8348 0.02596 0.01680 -0.0083 0.0281 1.0000
7.500 0.8507 0.02797 0.01906 -0.0060 0.0247 1.0000
7.750 0.8661 0.02955 0.02084 -0.0040 0.0194 1.0000
8.000 0.8782 0.03205 0.02358 -0.0018 0.0160 1.0000
8.250 0.8920 0.03485 0.02681 0.0006 0.0145 1.0000
8.500 0.9024 0.03741 0.02978 0.0031 0.0128 1.0000
8.750 0.9104 0.03928 0.03196 0.0055 0.0110 1.0000
9.000 0.9153 0.04117 0.03407 0.0080 0.0099 1.0000
9.750 0.8916 0.05084 0.04467 0.0183 0.0086 1.0000
10.000 0.8783 0.05379 0.04789 0.0215 0.0085 1.0000
10.250 0.8624 0.05723 0.05156 0.0236 0.0085 1.0000
10.500 0.8463 0.06101 0.05552 0.0245 0.0086 1.0000
10.750 0.8288 0.06549 0.06019 0.0237 0.0086 1.0000
11.000 0.8100 0.07115 0.06601 0.0208 0.0086 1.0000
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Polar data table (+)
Polar graphs
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