MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 62 9.3% (mh62-il) Reynolds number: 100,000 Max Cl/Cd: 45.99 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh62-il-100000-n5.txt Download as CSV file: xf-mh62-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 62 9.3%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5629 0.08877 0.08427 0.0012 1.0000 0.0178
-8.750 -0.5652 0.08333 0.07889 -0.0023 1.0000 0.0177
-8.500 -0.5690 0.07754 0.07316 -0.0064 1.0000 0.0175
-8.250 -0.5734 0.07178 0.06745 -0.0112 1.0000 0.0170
-8.000 -0.5818 0.06454 0.06017 -0.0177 1.0000 0.0166
-7.750 -0.5864 0.05868 0.05417 -0.0215 1.0000 0.0162
-7.500 -0.5885 0.05278 0.04800 -0.0244 1.0000 0.0163
-7.250 -0.5845 0.04774 0.04263 -0.0259 1.0000 0.0162
-7.000 -0.5763 0.04295 0.03740 -0.0267 1.0000 0.0162
-6.750 -0.5639 0.03869 0.03267 -0.0269 1.0000 0.0162
-6.500 -0.5479 0.03491 0.02838 -0.0267 1.0000 0.0162
-6.250 -0.5291 0.03161 0.02458 -0.0262 1.0000 0.0164
-6.000 -0.5080 0.02884 0.02135 -0.0257 1.0000 0.0167
-5.750 -0.4857 0.02648 0.01860 -0.0250 1.0000 0.0172
-5.500 -0.4634 0.02454 0.01635 -0.0242 1.0000 0.0178
-5.250 -0.4426 0.02299 0.01459 -0.0231 1.0000 0.0184
-5.000 -0.4147 0.02103 0.01249 -0.0237 0.9847 0.0202
-4.750 -0.3805 0.01990 0.01124 -0.0254 0.9706 0.0251
-4.500 -0.3482 0.01849 0.00966 -0.0264 0.9575 0.0298
-4.250 -0.3173 0.01734 0.00844 -0.0271 0.9449 0.0432
-4.000 -0.2896 0.01597 0.00735 -0.0274 0.9325 0.0937
-3.750 -0.2636 0.01498 0.00683 -0.0274 0.9203 0.2001
-3.500 -0.2382 0.01443 0.00652 -0.0271 0.9085 0.2861
-3.250 -0.2136 0.01402 0.00630 -0.0264 0.8970 0.3581
-3.000 -0.1892 0.01371 0.00609 -0.0254 0.8861 0.4174
-2.750 -0.1652 0.01342 0.00589 -0.0243 0.8749 0.4727
-2.500 -0.1410 0.01315 0.00572 -0.0233 0.8639 0.5280
-2.250 -0.1167 0.01289 0.00553 -0.0221 0.8533 0.5866
-2.000 -0.0924 0.01263 0.00540 -0.0208 0.8433 0.6501
-1.750 -0.0680 0.01238 0.00530 -0.0193 0.8332 0.7200
-1.500 -0.0395 0.01217 0.00522 -0.0185 0.8227 0.7978
-1.250 0.0007 0.01203 0.00508 -0.0200 0.8130 0.8757
-1.000 0.0471 0.01196 0.00489 -0.0230 0.8034 0.9349
-0.750 0.0923 0.01192 0.00470 -0.0263 0.7922 0.9760
-0.500 0.1303 0.01191 0.00452 -0.0284 0.7805 1.0000
-0.250 0.1532 0.01195 0.00443 -0.0274 0.7685 1.0000
0.000 0.1766 0.01199 0.00435 -0.0264 0.7564 1.0000
0.250 0.2002 0.01204 0.00429 -0.0255 0.7443 1.0000
0.500 0.2240 0.01210 0.00423 -0.0245 0.7320 1.0000
0.750 0.2481 0.01216 0.00419 -0.0236 0.7193 1.0000
1.000 0.2724 0.01222 0.00417 -0.0227 0.7060 1.0000
1.250 0.2970 0.01229 0.00416 -0.0219 0.6921 1.0000
1.500 0.3219 0.01237 0.00419 -0.0212 0.6775 1.0000
1.750 0.3469 0.01245 0.00421 -0.0205 0.6621 1.0000
2.000 0.3720 0.01254 0.00425 -0.0198 0.6460 1.0000
2.250 0.3972 0.01263 0.00429 -0.0190 0.6292 1.0000
2.500 0.4224 0.01273 0.00434 -0.0183 0.6120 1.0000
2.750 0.4477 0.01285 0.00444 -0.0176 0.5933 1.0000
3.000 0.4731 0.01299 0.00454 -0.0170 0.5735 1.0000
3.250 0.4984 0.01315 0.00464 -0.0163 0.5533 1.0000
3.500 0.5238 0.01333 0.00481 -0.0158 0.5315 1.0000
3.750 0.5491 0.01353 0.00497 -0.0152 0.5093 1.0000
4.000 0.5744 0.01378 0.00516 -0.0146 0.4865 1.0000
4.250 0.5996 0.01404 0.00539 -0.0140 0.4626 1.0000
4.500 0.6248 0.01434 0.00569 -0.0135 0.4389 1.0000
4.750 0.6497 0.01468 0.00598 -0.0130 0.4154 1.0000
5.000 0.6747 0.01504 0.00632 -0.0125 0.3912 1.0000
5.250 0.6995 0.01543 0.00669 -0.0121 0.3673 1.0000
5.500 0.7240 0.01586 0.00710 -0.0116 0.3438 1.0000
5.750 0.7483 0.01632 0.00759 -0.0111 0.3201 1.0000
6.000 0.7726 0.01680 0.00809 -0.0107 0.2964 1.0000
6.250 0.7964 0.01733 0.00862 -0.0102 0.2729 1.0000
6.500 0.8198 0.01791 0.00918 -0.0097 0.2504 1.0000
6.750 0.8431 0.01851 0.00982 -0.0092 0.2273 1.0000
7.000 0.8658 0.01917 0.01050 -0.0087 0.2059 1.0000
7.250 0.8880 0.01989 0.01129 -0.0081 0.1847 1.0000
7.500 0.9098 0.02066 0.01209 -0.0076 0.1646 1.0000
7.750 0.9309 0.02148 0.01294 -0.0070 0.1452 1.0000
8.000 0.9512 0.02239 0.01386 -0.0063 0.1268 1.0000
8.250 0.9711 0.02333 0.01488 -0.0056 0.1083 1.0000
8.500 0.9894 0.02442 0.01598 -0.0049 0.0909 1.0000
8.750 1.0066 0.02562 0.01720 -0.0040 0.0753 1.0000
9.000 1.0226 0.02693 0.01857 -0.0030 0.0614 1.0000
9.250 1.0357 0.02850 0.02017 -0.0019 0.0514 1.0000
9.500 1.0483 0.03003 0.02186 -0.0007 0.0424 1.0000
9.750 1.0582 0.03181 0.02380 0.0008 0.0368 1.0000
10.000 1.0657 0.03363 0.02574 0.0023 0.0323 1.0000
10.250 1.0695 0.03568 0.02792 0.0040 0.0285 1.0000
10.500 1.0725 0.03759 0.03002 0.0057 0.0254 1.0000
10.750 1.0726 0.03979 0.03234 0.0071 0.0234 1.0000
11.000 1.0695 0.04245 0.03508 0.0080 0.0217 1.0000
11.250 1.0680 0.04530 0.03814 0.0086 0.0199 1.0000
11.500 1.0669 0.04819 0.04127 0.0088 0.0183 1.0000
11.750 1.0635 0.05147 0.04477 0.0086 0.0173 1.0000
12.000 1.0580 0.05523 0.04872 0.0080 0.0165 1.0000
12.250 1.0514 0.05924 0.05291 0.0068 0.0160 1.0000
12.500 1.0438 0.06361 0.05745 0.0052 0.0156 1.0000
12.750 1.0335 0.06858 0.06257 0.0028 0.0151 1.0000
13.000 1.0221 0.07400 0.06814 0.0000 0.0147 1.0000
13.250 1.0107 0.07992 0.07428 -0.0030 0.0150 1.0000
13.500 0.9958 0.08661 0.08112 -0.0069 0.0146 1.0000
13.750 0.9795 0.09422 0.08893 -0.0114 0.0149 1.0000
14.000 0.9587 0.10343 0.09836 -0.0170 0.0152 1.0000
14.250 0.9307 0.11528 0.11042 -0.0241 0.0160 1.0000
14.500 0.9004 0.12881 0.12409 -0.0318 0.0173 1.0000
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Polar data table (+)
Polar graphs
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