MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 106 13.07% (mh106-il) Reynolds number: 200,000 Max Cl/Cd: 61.42 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh106-il-200000.txt Download as CSV file: xf-mh106-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 106 13.07%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.8313 0.05284 0.04823 -0.0259 1.0000 0.0243
-10.000 -0.8427 0.04922 0.04442 -0.0234 1.0000 0.0236
-9.750 -0.8494 0.04566 0.04060 -0.0209 1.0000 0.0229
-9.500 -0.8511 0.04240 0.03702 -0.0185 1.0000 0.0226
-9.250 -0.8472 0.03952 0.03383 -0.0162 1.0000 0.0225
-9.000 -0.8393 0.03685 0.03083 -0.0141 1.0000 0.0227
-8.750 -0.8280 0.03442 0.02810 -0.0121 1.0000 0.0230
-8.500 -0.8138 0.03180 0.02516 -0.0103 1.0000 0.0228
-8.250 -0.7965 0.02932 0.02237 -0.0087 1.0000 0.0225
-8.000 -0.7768 0.02721 0.02004 -0.0074 1.0000 0.0224
-7.750 -0.7559 0.02535 0.01802 -0.0061 1.0000 0.0226
-7.500 -0.7348 0.02375 0.01631 -0.0049 1.0000 0.0231
-7.250 -0.7143 0.02233 0.01481 -0.0035 1.0000 0.0238
-7.000 -0.6943 0.02115 0.01355 -0.0020 1.0000 0.0250
-6.750 -0.6794 0.01952 0.01192 0.0001 1.0000 0.0264
-6.500 -0.6633 0.01839 0.01081 0.0020 1.0000 0.0292
-6.250 -0.6447 0.01759 0.00995 0.0036 1.0000 0.0339
-6.000 -0.6302 0.01642 0.00878 0.0059 1.0000 0.0423
-5.750 -0.6224 0.01456 0.00730 0.0093 1.0000 0.0903
-5.500 -0.6159 0.01303 0.00667 0.0123 1.0000 0.2347
-5.250 -0.5883 0.01266 0.00647 0.0118 0.9924 0.2905
-5.000 -0.5424 0.01236 0.00626 0.0078 0.9692 0.3381
-4.750 -0.4987 0.01213 0.00603 0.0046 0.9384 0.3717
-4.500 -0.4597 0.01195 0.00581 0.0026 0.9026 0.4022
-4.250 -0.4308 0.01182 0.00561 0.0028 0.8659 0.4266
-4.000 -0.4069 0.01171 0.00538 0.0041 0.8318 0.4462
-3.750 -0.3835 0.01162 0.00515 0.0053 0.8021 0.4658
-3.500 -0.3600 0.01148 0.00495 0.0066 0.7757 0.4850
-3.250 -0.3360 0.01135 0.00475 0.0076 0.7517 0.5062
-3.000 -0.3118 0.01122 0.00457 0.0086 0.7298 0.5289
-2.750 -0.2875 0.01110 0.00441 0.0096 0.7091 0.5541
-2.500 -0.2634 0.01098 0.00427 0.0106 0.6905 0.5809
-2.250 -0.2390 0.01085 0.00416 0.0116 0.6726 0.6105
-2.000 -0.2145 0.01074 0.00407 0.0125 0.6559 0.6431
-1.750 -0.1900 0.01064 0.00402 0.0135 0.6407 0.6772
-1.500 -0.1652 0.01056 0.00399 0.0145 0.6266 0.7132
-1.250 -0.1400 0.01052 0.00398 0.0155 0.6134 0.7497
-1.000 -0.1137 0.01052 0.00400 0.0163 0.6010 0.7851
-0.750 -0.0860 0.01055 0.00407 0.0169 0.5888 0.8189
-0.500 -0.0562 0.01065 0.00417 0.0170 0.5778 0.8494
-0.250 -0.0226 0.01083 0.00430 0.0164 0.5677 0.8748
0.000 0.0119 0.01103 0.00442 0.0155 0.5576 0.8971
0.250 0.0507 0.01127 0.00460 0.0137 0.5476 0.9137
0.500 0.0901 0.01155 0.00478 0.0118 0.5392 0.9279
0.750 0.1299 0.01179 0.00495 0.0097 0.5302 0.9404
1.000 0.1778 0.01205 0.00514 0.0058 0.5217 0.9475
1.250 0.2200 0.01227 0.00527 0.0031 0.5141 0.9574
1.500 0.2624 0.01247 0.00543 0.0002 0.5061 0.9672
1.750 0.3085 0.01261 0.00549 -0.0036 0.4990 0.9746
2.000 0.3521 0.01274 0.00563 -0.0069 0.4914 0.9836
2.250 0.3978 0.01281 0.00563 -0.0107 0.4843 0.9913
2.500 0.4438 0.01283 0.00566 -0.0147 0.4768 0.9986
2.750 0.4705 0.01286 0.00566 -0.0148 0.4706 1.0000
3.000 0.4924 0.01295 0.00574 -0.0140 0.4652 1.0000
3.250 0.5144 0.01301 0.00583 -0.0132 0.4587 1.0000
3.500 0.5370 0.01313 0.00589 -0.0123 0.4535 1.0000
3.750 0.5592 0.01322 0.00607 -0.0115 0.4467 1.0000
4.000 0.5818 0.01333 0.00615 -0.0106 0.4406 1.0000
4.250 0.6044 0.01348 0.00635 -0.0098 0.4341 1.0000
4.500 0.6271 0.01359 0.00647 -0.0089 0.4271 1.0000
4.750 0.6499 0.01375 0.00665 -0.0080 0.4205 1.0000
5.000 0.6727 0.01386 0.00680 -0.0071 0.4131 1.0000
5.250 0.6955 0.01401 0.00699 -0.0062 0.4058 1.0000
5.500 0.7184 0.01413 0.00714 -0.0053 0.3979 1.0000
5.750 0.7412 0.01428 0.00735 -0.0044 0.3900 1.0000
6.000 0.7643 0.01439 0.00745 -0.0035 0.3816 1.0000
6.250 0.7868 0.01452 0.00770 -0.0025 0.3723 1.0000
6.500 0.8096 0.01464 0.00783 -0.0015 0.3632 1.0000
6.750 0.8322 0.01472 0.00798 -0.0005 0.3528 1.0000
7.000 0.8544 0.01482 0.00817 0.0005 0.3410 1.0000
7.250 0.8766 0.01491 0.00835 0.0015 0.3285 1.0000
7.500 0.8985 0.01502 0.00854 0.0026 0.3143 1.0000
7.750 0.9202 0.01515 0.00873 0.0037 0.2982 1.0000
8.000 0.9410 0.01535 0.00893 0.0048 0.2796 1.0000
8.250 0.9613 0.01565 0.00927 0.0060 0.2565 1.0000
8.500 0.9797 0.01615 0.00971 0.0074 0.2324 1.0000
8.750 0.9961 0.01684 0.01032 0.0090 0.2085 1.0000
9.000 1.0121 0.01760 0.01103 0.0105 0.1858 1.0000
9.250 1.0260 0.01850 0.01184 0.0123 0.1663 1.0000
9.500 1.0402 0.01936 0.01270 0.0141 0.1487 1.0000
9.750 1.0529 0.02030 0.01362 0.0159 0.1334 1.0000
10.000 1.0641 0.02130 0.01461 0.0179 0.1203 1.0000
10.250 1.0736 0.02237 0.01567 0.0201 0.1088 1.0000
10.500 1.0802 0.02354 0.01680 0.0224 0.0988 1.0000
10.750 1.0870 0.02462 0.01795 0.0247 0.0895 1.0000
11.000 1.0890 0.02577 0.01917 0.0276 0.0820 1.0000
11.250 1.0859 0.02722 0.02060 0.0305 0.0760 1.0000
11.500 1.0868 0.02877 0.02225 0.0323 0.0699 1.0000
11.750 1.0852 0.03074 0.02424 0.0334 0.0648 1.0000
12.000 1.0839 0.03299 0.02657 0.0341 0.0597 1.0000
12.250 1.0842 0.03530 0.02896 0.0342 0.0551 1.0000
12.500 1.0786 0.03822 0.03183 0.0345 0.0512 1.0000
12.750 1.0800 0.04075 0.03454 0.0340 0.0471 1.0000
13.000 1.0776 0.04369 0.03752 0.0334 0.0436 1.0000
13.250 1.0725 0.04681 0.04063 0.0334 0.0404 1.0000
13.500 1.0713 0.04984 0.04383 0.0326 0.0375 1.0000
13.750 1.0684 0.05304 0.04710 0.0316 0.0349 1.0000
14.000 1.0638 0.05628 0.05031 0.0312 0.0327 1.0000
14.250 1.0610 0.05945 0.05362 0.0309 0.0308 1.0000
14.500 1.0567 0.06311 0.05743 0.0296 0.0288 1.0000
14.750 1.0530 0.06667 0.06108 0.0282 0.0271 1.0000
15.000 1.0492 0.07032 0.06475 0.0269 0.0257 1.0000
15.250 1.0442 0.07392 0.06838 0.0265 0.0239 1.0000
15.500 1.0396 0.07805 0.07269 0.0250 0.0232 1.0000
15.750 1.0335 0.08251 0.07732 0.0232 0.0223 1.0000
16.000 1.0266 0.08719 0.08214 0.0212 0.0214 1.0000
16.250 1.0203 0.09185 0.08695 0.0192 0.0210 1.0000
16.500 1.0142 0.09661 0.09177 0.0167 0.0199 1.0000
16.750 1.0103 0.10087 0.09604 0.0146 0.0189 1.0000
17.000 0.9981 0.10652 0.10178 0.0125 0.0181 1.0000
17.250 0.9871 0.11254 0.10796 0.0095 0.0181 1.0000
17.500 0.9711 0.12009 0.11569 0.0048 0.0176 1.0000
17.750 0.9570 0.12692 0.12267 0.0017 0.0180 1.0000
18.000 0.9396 0.13538 0.13130 -0.0037 0.0177 1.0000
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Polar data table (+)
Polar graphs
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