MH 20 9.01% (mh20-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 20 9.01% (mh20-il) Reynolds number: 200,000 Max Cl/Cd: 64.62 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh20-il-200000-n5.txt Download as CSV file: xf-mh20-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 20 9.01%
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 -0.5128 0.08627 0.08320 -0.0046 1.0000 0.0109
-8.250 -0.5153 0.08146 0.07845 -0.0077 1.0000 0.0106
-8.000 -0.5209 0.07637 0.07343 -0.0117 1.0000 0.0102
-7.750 -0.5277 0.07105 0.06815 -0.0162 1.0000 0.0100
-7.500 -0.5292 0.06472 0.06179 -0.0212 1.0000 0.0096
-7.250 -0.5278 0.05589 0.05279 -0.0269 0.9564 0.0089
-7.000 -0.5234 0.04670 0.04321 -0.0296 0.9178 0.0081
-6.750 -0.5152 0.04194 0.03807 -0.0289 0.8949 0.0077
-6.500 -0.5043 0.03857 0.03433 -0.0277 0.8779 0.0075
-6.250 -0.4908 0.03567 0.03106 -0.0265 0.8642 0.0074
-6.000 -0.4759 0.03284 0.02783 -0.0252 0.8520 0.0073
-5.750 -0.4613 0.02952 0.02399 -0.0237 0.8412 0.0071
-5.500 -0.4443 0.02644 0.02040 -0.0222 0.8318 0.0071
-5.250 -0.4245 0.02389 0.01736 -0.0208 0.8231 0.0070
-5.000 -0.4023 0.02176 0.01474 -0.0197 0.8149 0.0070
-4.500 -0.3548 0.01847 0.01082 -0.0177 0.7999 0.0071
-4.250 -0.3308 0.01723 0.00934 -0.0167 0.7936 0.0072
-4.000 -0.3069 0.01588 0.00781 -0.0158 0.7864 0.0075
-3.750 -0.2831 0.01485 0.00652 -0.0147 0.7806 0.0083
-3.500 -0.2575 0.01415 0.00565 -0.0141 0.7737 0.0098
-3.250 -0.2318 0.01360 0.00494 -0.0134 0.7682 0.0144
-3.000 -0.2081 0.01265 0.00443 -0.0129 0.7619 0.0845
-2.750 -0.1839 0.01204 0.00409 -0.0124 0.7562 0.1631
-2.500 -0.1583 0.01167 0.00382 -0.0120 0.7505 0.2140
-2.250 -0.1333 0.01124 0.00359 -0.0116 0.7445 0.2836
-2.000 -0.1093 0.01079 0.00337 -0.0109 0.7390 0.3683
-1.750 -0.0866 0.01023 0.00321 -0.0100 0.7325 0.4844
-1.500 -0.0667 0.00959 0.00307 -0.0082 0.7273 0.6335
-1.250 -0.0355 0.00897 0.00308 -0.0081 0.7208 0.8188
-1.000 0.0401 0.00897 0.00304 -0.0175 0.7152 0.9297
-0.750 0.0817 0.00907 0.00302 -0.0201 0.7086 0.9592
-0.500 0.1185 0.00916 0.00297 -0.0219 0.7023 0.9794
-0.250 0.1620 0.00918 0.00286 -0.0253 0.6958 0.9926
0.000 0.2021 0.00915 0.00274 -0.0280 0.6892 1.0000
0.250 0.2273 0.00917 0.00268 -0.0275 0.6825 1.0000
0.500 0.2525 0.00919 0.00263 -0.0270 0.6758 1.0000
0.750 0.2780 0.00922 0.00261 -0.0266 0.6688 1.0000
1.000 0.3033 0.00925 0.00258 -0.0261 0.6618 1.0000
1.250 0.3289 0.00929 0.00259 -0.0257 0.6542 1.0000
1.500 0.3543 0.00934 0.00259 -0.0252 0.6470 1.0000
1.750 0.3802 0.00938 0.00264 -0.0248 0.6382 1.0000
2.000 0.4058 0.00943 0.00267 -0.0244 0.6301 1.0000
2.250 0.4314 0.00949 0.00271 -0.0239 0.6210 1.0000
2.500 0.4572 0.00955 0.00278 -0.0236 0.6110 1.0000
2.750 0.4829 0.00961 0.00285 -0.0231 0.6006 1.0000
3.000 0.5086 0.00968 0.00297 -0.0227 0.5892 1.0000
3.250 0.5343 0.00975 0.00306 -0.0222 0.5763 1.0000
3.500 0.5600 0.00983 0.00316 -0.0218 0.5615 1.0000
3.750 0.5855 0.00993 0.00327 -0.0213 0.5442 1.0000
4.000 0.6109 0.01004 0.00343 -0.0208 0.5241 1.0000
4.250 0.6360 0.01019 0.00356 -0.0203 0.5005 1.0000
4.500 0.6608 0.01040 0.00372 -0.0198 0.4741 1.0000
4.750 0.6852 0.01067 0.00393 -0.0192 0.4462 1.0000
5.000 0.7094 0.01099 0.00420 -0.0186 0.4178 1.0000
5.250 0.7334 0.01135 0.00451 -0.0180 0.3885 1.0000
5.500 0.7569 0.01177 0.00487 -0.0175 0.3558 1.0000
5.750 0.7798 0.01226 0.00534 -0.0168 0.3183 1.0000
6.000 0.8016 0.01288 0.00581 -0.0161 0.2720 1.0000
6.250 0.8218 0.01368 0.00637 -0.0154 0.2122 1.0000
6.500 0.8406 0.01468 0.00705 -0.0145 0.1489 1.0000
6.750 0.8590 0.01570 0.00784 -0.0135 0.0977 1.0000
7.000 0.8732 0.01720 0.00892 -0.0121 0.0387 1.0000
7.250 0.8885 0.01852 0.01008 -0.0106 0.0160 1.0000
7.500 0.9042 0.01974 0.01135 -0.0090 0.0084 1.0000
7.750 0.9207 0.02080 0.01260 -0.0075 0.0065 1.0000
8.000 0.9358 0.02192 0.01389 -0.0058 0.0059 1.0000
8.250 0.9493 0.02315 0.01526 -0.0041 0.0052 1.0000
8.500 0.9613 0.02445 0.01670 -0.0022 0.0049 1.0000
8.750 0.9705 0.02601 0.01840 0.0000 0.0046 1.0000
9.000 0.9786 0.02770 0.02033 0.0022 0.0044 1.0000
9.250 0.9864 0.02949 0.02227 0.0044 0.0043 1.0000
9.500 0.9915 0.03156 0.02451 0.0069 0.0042 1.0000
9.750 0.9976 0.03338 0.02650 0.0091 0.0042 1.0000
10.000 1.0004 0.03597 0.02932 0.0114 0.0041 1.0000
10.250 1.0024 0.03855 0.03214 0.0133 0.0041 1.0000
10.500 0.9997 0.04163 0.03550 0.0151 0.0040 1.0000
10.750 0.9967 0.04451 0.03862 0.0165 0.0040 1.0000
11.000 0.9961 0.04690 0.04121 0.0172 0.0040 1.0000
11.250 0.9873 0.05055 0.04511 0.0178 0.0040 1.0000
11.500 0.9744 0.05486 0.04967 0.0176 0.0040 1.0000
11.750 0.9665 0.05854 0.05354 0.0170 0.0040 1.0000
12.000 0.9535 0.06321 0.05842 0.0157 0.0040 1.0000
12.250 0.9481 0.06693 0.06230 0.0142 0.0041 1.0000
12.500 0.9318 0.07276 0.06831 0.0115 0.0041 1.0000
12.750 0.9215 0.07799 0.07371 0.0086 0.0041 1.0000
13.000 0.9058 0.08469 0.08057 0.0047 0.0041 1.0000
13.250 0.8916 0.09176 0.08779 0.0004 0.0041 1.0000
13.500 0.8825 0.09833 0.09449 -0.0036 0.0042 1.0000
13.750 0.8662 0.10724 0.10352 -0.0090 0.0043 1.0000
14.000 0.8512 0.11654 0.11292 -0.0144 0.0043 1.0000
14.250 0.8307 0.12886 0.12535 -0.0208 0.0045 1.0000
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Polar data table (+)
Polar graphs
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