MH33 (mh33-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH33 (mh33-il) Reynolds number: 100,000 Max Cl/Cd: 42.16 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh33-il-100000-n5.txt Download as CSV file: xf-mh33-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH33
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 -0.4503 0.10452 0.09971 -0.0094 1.0000 0.0234
-9.750 -0.5377 0.10698 0.10186 -0.0069 1.0000 0.0247
-9.500 -0.5361 0.10277 0.09769 -0.0083 1.0000 0.0232
-9.250 -0.5351 0.09867 0.09363 -0.0100 1.0000 0.0222
-9.000 -0.5361 0.09403 0.08904 -0.0122 1.0000 0.0211
-8.750 -0.5379 0.08938 0.08446 -0.0146 1.0000 0.0202
-8.500 -0.5423 0.08408 0.07923 -0.0178 1.0000 0.0193
-8.000 -0.5533 0.07087 0.06611 -0.0286 1.0000 0.0173
-7.750 -0.5514 0.06664 0.06177 -0.0303 1.0000 0.0168
-7.500 -0.5549 0.06204 0.05711 -0.0315 1.0000 0.0165
-7.250 -0.5561 0.05752 0.05247 -0.0323 1.0000 0.0163
-7.000 -0.5552 0.05304 0.04782 -0.0325 1.0000 0.0161
-6.750 -0.5518 0.04872 0.04326 -0.0322 1.0000 0.0159
-6.500 -0.5461 0.04461 0.03885 -0.0314 1.0000 0.0156
-6.250 -0.5377 0.04075 0.03465 -0.0302 1.0000 0.0155
-6.000 -0.5269 0.03714 0.03063 -0.0288 1.0000 0.0153
-5.750 -0.5135 0.03377 0.02681 -0.0272 1.0000 0.0152
-5.500 -0.4978 0.03074 0.02331 -0.0255 1.0000 0.0151
-5.250 -0.4799 0.02805 0.02016 -0.0239 1.0000 0.0151
-5.000 -0.4602 0.02569 0.01739 -0.0223 1.0000 0.0152
-4.750 -0.4394 0.02363 0.01487 -0.0208 1.0000 0.0155
-4.500 -0.4180 0.02189 0.01287 -0.0193 1.0000 0.0159
-4.250 -0.3967 0.02038 0.01115 -0.0178 1.0000 0.0165
-4.000 -0.3762 0.01892 0.00955 -0.0163 1.0000 0.0178
-3.750 -0.3554 0.01791 0.00848 -0.0152 1.0000 0.0236
-3.500 -0.3341 0.01685 0.00727 -0.0138 1.0000 0.0295
-3.250 -0.3128 0.01559 0.00616 -0.0125 1.0000 0.0619
-3.000 -0.2930 0.01418 0.00552 -0.0115 1.0000 0.1960
-2.750 -0.2726 0.01326 0.00518 -0.0105 1.0000 0.3340
-2.500 -0.2523 0.01253 0.00494 -0.0092 1.0000 0.4693
-2.250 -0.2328 0.01192 0.00474 -0.0072 1.0000 0.6064
-2.000 -0.2137 0.01146 0.00475 -0.0045 1.0000 0.7534
-1.750 -0.1641 0.01140 0.00483 -0.0074 1.0000 0.9263
-1.500 -0.0977 0.01141 0.00456 -0.0152 1.0000 0.9958
-1.250 -0.0783 0.01142 0.00437 -0.0140 1.0000 1.0000
-1.000 -0.0628 0.01145 0.00426 -0.0120 1.0000 1.0000
-0.750 -0.0465 0.01151 0.00420 -0.0102 1.0000 1.0000
-0.500 -0.0102 0.01164 0.00421 -0.0124 0.9940 1.0000
-0.250 0.0326 0.01176 0.00422 -0.0158 0.9847 1.0000
0.000 0.0748 0.01185 0.00421 -0.0190 0.9748 1.0000
0.250 0.1176 0.01191 0.00423 -0.0222 0.9645 1.0000
0.500 0.1618 0.01193 0.00424 -0.0257 0.9540 1.0000
0.750 0.2044 0.01190 0.00422 -0.0287 0.9417 1.0000
1.000 0.2407 0.01183 0.00417 -0.0303 0.9254 1.0000
1.250 0.2753 0.01176 0.00413 -0.0314 0.9068 1.0000
1.500 0.3104 0.01167 0.00408 -0.0325 0.8862 1.0000
1.750 0.3438 0.01159 0.00407 -0.0332 0.8612 1.0000
2.000 0.3749 0.01152 0.00402 -0.0333 0.8304 1.0000
2.250 0.4065 0.01147 0.00396 -0.0334 0.7942 1.0000
2.500 0.4352 0.01151 0.00394 -0.0329 0.7502 1.0000
2.750 0.4617 0.01164 0.00396 -0.0319 0.7002 1.0000
3.000 0.4859 0.01188 0.00411 -0.0307 0.6452 1.0000
3.250 0.5087 0.01222 0.00427 -0.0292 0.5873 1.0000
3.500 0.5305 0.01262 0.00448 -0.0278 0.5289 1.0000
3.750 0.5519 0.01309 0.00475 -0.0263 0.4708 1.0000
4.000 0.5732 0.01360 0.00507 -0.0250 0.4138 1.0000
4.250 0.5945 0.01415 0.00552 -0.0238 0.3589 1.0000
4.500 0.6158 0.01475 0.00595 -0.0226 0.3055 1.0000
4.750 0.6370 0.01540 0.00643 -0.0215 0.2550 1.0000
5.000 0.6585 0.01607 0.00698 -0.0205 0.2083 1.0000
5.250 0.6800 0.01681 0.00761 -0.0195 0.1679 1.0000
5.500 0.7012 0.01762 0.00831 -0.0186 0.1307 1.0000
5.750 0.7223 0.01851 0.00914 -0.0175 0.1014 1.0000
6.000 0.7430 0.01948 0.01004 -0.0165 0.0749 1.0000
6.250 0.7629 0.02063 0.01128 -0.0153 0.0585 1.0000
6.500 0.7826 0.02180 0.01245 -0.0141 0.0445 1.0000
6.750 0.8025 0.02308 0.01394 -0.0127 0.0376 1.0000
7.000 0.8196 0.02495 0.01586 -0.0111 0.0331 1.0000
7.250 0.8402 0.02671 0.01794 -0.0097 0.0296 1.0000
7.500 0.8594 0.02796 0.01934 -0.0087 0.0240 1.0000
7.750 0.8758 0.03096 0.02261 -0.0070 0.0215 1.0000
8.000 0.8933 0.03346 0.02561 -0.0054 0.0185 1.0000
8.250 0.9086 0.03504 0.02745 -0.0042 0.0152 1.0000
8.500 0.9188 0.03791 0.03061 -0.0026 0.0139 1.0000
8.750 0.9195 0.04267 0.03585 -0.0003 0.0131 1.0000
9.000 0.9213 0.04637 0.04005 0.0018 0.0128 1.0000
9.250 0.9167 0.05038 0.04451 0.0039 0.0125 1.0000
9.500 0.9085 0.05416 0.04861 0.0056 0.0125 1.0000
9.750 0.8913 0.05802 0.05275 0.0076 0.0124 1.0000
10.000 0.8760 0.06183 0.05673 0.0080 0.0126 1.0000
10.250 0.8562 0.06699 0.06207 0.0059 0.0126 1.0000
10.500 0.8396 0.07301 0.06821 0.0016 0.0127 1.0000
10.750 0.8232 0.08079 0.07608 -0.0047 0.0129 1.0000
11.000 0.8095 0.08917 0.08448 -0.0108 0.0131 1.0000
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Polar data table (+)
Polar graphs
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