MH 110 10.01% (mh110-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 110 10.01% (mh110-il) Reynolds number: 100,000 Max Cl/Cd: 41.03 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh110-il-100000-n5.txt Download as CSV file: xf-mh110-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 110 10.01%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6621 0.09152 0.08704 0.0166 1.0000 0.0145
-9.500 -0.6854 0.07625 0.07174 0.0057 1.0000 0.0133
-9.250 -0.7028 0.06898 0.06433 -0.0004 1.0000 0.0130
-9.000 -0.7167 0.06465 0.05985 -0.0020 1.0000 0.0129
-8.750 -0.7323 0.06076 0.05577 -0.0013 1.0000 0.0128
-8.500 -0.7423 0.05672 0.05153 -0.0004 1.0000 0.0127
-8.250 -0.7476 0.05272 0.04725 0.0007 1.0000 0.0127
-8.000 -0.7484 0.04879 0.04300 0.0021 1.0000 0.0126
-7.750 -0.7453 0.04498 0.03880 0.0037 1.0000 0.0126
-7.500 -0.7380 0.04144 0.03484 0.0053 1.0000 0.0127
-7.250 -0.7268 0.03823 0.03121 0.0070 1.0000 0.0127
-7.000 -0.7125 0.03530 0.02784 0.0085 1.0000 0.0128
-6.750 -0.6970 0.03215 0.02431 0.0101 1.0000 0.0132
-6.500 -0.6792 0.02980 0.02174 0.0112 1.0000 0.0142
-6.250 -0.6585 0.02828 0.02004 0.0121 1.0000 0.0156
-6.000 -0.6362 0.02663 0.01810 0.0131 1.0000 0.0172
-5.750 -0.6130 0.02490 0.01614 0.0142 1.0000 0.0186
-5.500 -0.5900 0.02324 0.01430 0.0154 1.0000 0.0197
-5.250 -0.5689 0.02161 0.01256 0.0168 1.0000 0.0211
-5.000 -0.5479 0.02032 0.01123 0.0179 1.0000 0.0246
-4.750 -0.5254 0.01933 0.01013 0.0191 1.0000 0.0307
-4.500 -0.5041 0.01814 0.00889 0.0205 1.0000 0.0412
-4.250 -0.4839 0.01679 0.00786 0.0218 1.0000 0.0796
-4.000 -0.4642 0.01555 0.00714 0.0229 1.0000 0.1646
-3.750 -0.4440 0.01457 0.00667 0.0240 1.0000 0.2604
-3.500 -0.4238 0.01376 0.00629 0.0253 1.0000 0.3533
-3.250 -0.4037 0.01306 0.00600 0.0267 1.0000 0.4462
-3.000 -0.3682 0.01243 0.00577 0.0254 0.9271 0.5577
-2.750 -0.3287 0.01207 0.00564 0.0241 0.8586 0.6655
-2.500 -0.2958 0.01202 0.00556 0.0245 0.8040 0.7460
-2.250 -0.2604 0.01215 0.00555 0.0244 0.7583 0.8059
-2.000 -0.2231 0.01237 0.00553 0.0237 0.7177 0.8481
-1.750 -0.1854 0.01262 0.00550 0.0226 0.6808 0.8788
-1.500 -0.1486 0.01286 0.00543 0.0216 0.6482 0.9033
-1.250 -0.1099 0.01309 0.00538 0.0200 0.6174 0.9229
-1.000 -0.0717 0.01330 0.00534 0.0184 0.5892 0.9403
-0.750 -0.0324 0.01348 0.00525 0.0163 0.5629 0.9552
-0.500 0.0079 0.01362 0.00515 0.0140 0.5379 0.9683
-0.250 0.0495 0.01369 0.00501 0.0111 0.5142 0.9796
0.000 0.0909 0.01373 0.00482 0.0082 0.4929 0.9896
0.250 0.1322 0.01372 0.00465 0.0053 0.4722 0.9989
0.500 0.1574 0.01375 0.00454 0.0055 0.4562 1.0000
0.750 0.1804 0.01380 0.00447 0.0062 0.4417 1.0000
1.000 0.2035 0.01387 0.00443 0.0070 0.4279 1.0000
1.250 0.2269 0.01396 0.00442 0.0077 0.4152 1.0000
1.500 0.2504 0.01406 0.00443 0.0084 0.4032 1.0000
1.750 0.2739 0.01419 0.00449 0.0091 0.3919 1.0000
2.000 0.2975 0.01434 0.00454 0.0098 0.3814 1.0000
2.250 0.3213 0.01450 0.00465 0.0104 0.3710 1.0000
2.500 0.3452 0.01468 0.00479 0.0111 0.3617 1.0000
2.750 0.3690 0.01488 0.00495 0.0118 0.3536 1.0000
3.000 0.3931 0.01508 0.00516 0.0124 0.3446 1.0000
3.250 0.4170 0.01531 0.00536 0.0131 0.3368 1.0000
3.500 0.4411 0.01555 0.00559 0.0138 0.3293 1.0000
3.750 0.4652 0.01582 0.00590 0.0144 0.3227 1.0000
4.000 0.4893 0.01610 0.00619 0.0150 0.3162 1.0000
4.250 0.5134 0.01641 0.00650 0.0157 0.3103 1.0000
4.500 0.5376 0.01671 0.00687 0.0163 0.3038 1.0000
4.750 0.5615 0.01705 0.00722 0.0170 0.2988 1.0000
5.000 0.5858 0.01741 0.00772 0.0176 0.2930 1.0000
5.250 0.6099 0.01778 0.00814 0.0182 0.2881 1.0000
5.500 0.6339 0.01818 0.00860 0.0188 0.2834 1.0000
5.750 0.6580 0.01859 0.00916 0.0194 0.2777 1.0000
6.000 0.6820 0.01901 0.00969 0.0201 0.2734 1.0000
6.250 0.7059 0.01949 0.01029 0.0207 0.2689 1.0000
6.500 0.7296 0.01996 0.01096 0.0213 0.2635 1.0000
6.750 0.7534 0.02040 0.01147 0.0220 0.2590 1.0000
7.000 0.7768 0.02092 0.01221 0.0227 0.2533 1.0000
7.250 0.8001 0.02133 0.01277 0.0234 0.2468 1.0000
7.500 0.8229 0.02172 0.01336 0.0241 0.2392 1.0000
7.750 0.8458 0.02190 0.01365 0.0249 0.2303 1.0000
8.000 0.8678 0.02209 0.01409 0.0257 0.2181 1.0000
8.250 0.8896 0.02220 0.01440 0.0265 0.2038 1.0000
8.500 0.9111 0.02241 0.01486 0.0272 0.1855 1.0000
8.750 0.9323 0.02272 0.01535 0.0280 0.1620 1.0000
9.000 0.9510 0.02349 0.01614 0.0287 0.1174 1.0000
9.250 0.9588 0.02581 0.01807 0.0297 0.0694 1.0000
9.500 0.9638 0.02842 0.02060 0.0309 0.0487 1.0000
9.750 0.9671 0.03093 0.02319 0.0321 0.0384 1.0000
10.000 0.9704 0.03319 0.02565 0.0333 0.0325 1.0000
10.250 0.9646 0.03608 0.02869 0.0342 0.0286 1.0000
10.500 0.9535 0.03908 0.03182 0.0349 0.0271 1.0000
10.750 0.9406 0.04306 0.03598 0.0333 0.0257 1.0000
11.000 0.9280 0.04795 0.04102 0.0305 0.0248 1.0000
11.250 0.9167 0.05285 0.04603 0.0279 0.0242 1.0000
11.500 0.9074 0.05740 0.05069 0.0258 0.0238 1.0000
11.750 0.8981 0.06193 0.05531 0.0238 0.0229 1.0000
12.000 0.8895 0.06637 0.05981 0.0220 0.0219 1.0000
12.250 0.8819 0.07069 0.06419 0.0203 0.0209 1.0000
12.500 0.8750 0.07486 0.06839 0.0188 0.0199 1.0000
12.750 0.8720 0.07806 0.07158 0.0183 0.0187 1.0000
13.000 0.8698 0.08181 0.07547 0.0170 0.0181 1.0000
13.250 0.8641 0.08634 0.08016 0.0151 0.0169 1.0000
13.500 0.8614 0.09042 0.08434 0.0136 0.0164 1.0000
13.750 0.8551 0.09543 0.08947 0.0114 0.0153 1.0000
14.000 0.8514 0.10000 0.09416 0.0095 0.0150 1.0000
14.250 0.8452 0.10525 0.09952 0.0072 0.0145 1.0000
14.500 0.8383 0.11085 0.10524 0.0046 0.0143 1.0000
14.750 0.8298 0.11707 0.11159 0.0017 0.0143 1.0000
15.000 0.8191 0.12402 0.11865 -0.0017 0.0141 1.0000
15.250 0.8059 0.13206 0.12682 -0.0057 0.0145 1.0000
15.500 0.7894 0.14142 0.13629 -0.0102 0.0148 1.0000
15.750 0.7701 0.15247 0.14739 -0.0153 0.0152 1.0000
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Polar data table (+)
Polar graphs
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