MH 81 13% (mh81-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 81 13% (mh81-il) Reynolds number: 200,000 Max Cl/Cd: 51.97 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh81-il-200000.txt Download as CSV file: xf-mh81-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 81 13%
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4006 0.08826 0.08564 0.0001 0.9316 0.0505
-8.000 -0.4308 0.08045 0.07767 -0.0125 0.8528 0.0519
-7.750 -0.4614 0.07451 0.07138 -0.0179 0.8236 0.0521
-7.500 -0.4392 0.07251 0.06946 -0.0137 0.7968 0.0529
-7.250 -0.4279 0.07076 0.06765 -0.0118 0.7737 0.0538
-7.000 -0.4219 0.06786 0.06464 -0.0122 0.7542 0.0549
-6.750 -0.4180 0.06407 0.06069 -0.0139 0.7379 0.0568
-6.500 -0.4288 0.05658 0.05268 -0.0184 0.7286 0.0611
-6.250 -0.4118 0.05435 0.05045 -0.0177 0.7118 0.0621
-6.000 -0.3964 0.05204 0.04803 -0.0174 0.6963 0.0642
-5.750 -0.3893 0.04736 0.04280 -0.0183 0.6850 0.0708
-5.500 -0.3699 0.04511 0.04053 -0.0178 0.6708 0.0724
-5.250 -0.3553 0.04247 0.03731 -0.0175 0.6590 0.0812
-5.000 -0.3389 0.02890 0.02230 -0.0146 0.6545 0.0353
-4.750 -0.3151 0.02485 0.01713 -0.0124 0.6430 0.0289
-4.500 -0.2889 0.02322 0.01522 -0.0116 0.6297 0.0285
-4.250 -0.2625 0.02168 0.01340 -0.0108 0.6174 0.0284
-4.000 -0.2356 0.02046 0.01189 -0.0101 0.6053 0.0286
-3.750 -0.2087 0.01908 0.01046 -0.0095 0.5924 0.0295
-3.500 -0.1821 0.01818 0.00950 -0.0089 0.5807 0.0307
-3.250 -0.1550 0.01763 0.00874 -0.0083 0.5696 0.0335
-3.000 -0.1288 0.01681 0.00800 -0.0078 0.5574 0.0372
-2.750 -0.1029 0.01605 0.00721 -0.0071 0.5468 0.0413
-2.500 -0.0768 0.01538 0.00650 -0.0065 0.5363 0.0487
-2.250 -0.0512 0.01450 0.00580 -0.0058 0.5259 0.0825
-2.000 -0.0282 0.01340 0.00537 -0.0051 0.5169 0.2388
-1.750 -0.0050 0.01258 0.00521 -0.0045 0.5063 0.3938
-1.500 0.0121 0.01153 0.00511 -0.0021 0.4982 0.6389
-1.250 0.0356 0.01115 0.00543 0.0009 0.4880 0.8686
-1.000 0.0791 0.01147 0.00560 -0.0004 0.4778 0.9439
-0.750 0.1397 0.01173 0.00556 -0.0059 0.4660 0.9706
-0.500 0.2036 0.01182 0.00541 -0.0126 0.4532 0.9864
-0.250 0.2631 0.01186 0.00520 -0.0188 0.4424 1.0000
0.000 0.2872 0.01190 0.00510 -0.0182 0.4347 1.0000
0.250 0.3113 0.01201 0.00505 -0.0175 0.4277 1.0000
0.500 0.3356 0.01207 0.00502 -0.0169 0.4199 1.0000
0.750 0.3597 0.01224 0.00499 -0.0162 0.4137 1.0000
1.000 0.3843 0.01232 0.00505 -0.0156 0.4062 1.0000
1.250 0.4086 0.01245 0.00506 -0.0149 0.4001 1.0000
1.500 0.4329 0.01266 0.00515 -0.0143 0.3944 1.0000
1.750 0.4575 0.01280 0.00525 -0.0137 0.3879 1.0000
2.000 0.4818 0.01297 0.00530 -0.0130 0.3824 1.0000
2.250 0.5063 0.01320 0.00547 -0.0124 0.3769 1.0000
2.500 0.5308 0.01338 0.00561 -0.0117 0.3711 1.0000
2.750 0.5553 0.01359 0.00573 -0.0111 0.3665 1.0000
3.000 0.5798 0.01389 0.00595 -0.0104 0.3619 1.0000
3.250 0.6044 0.01409 0.00617 -0.0099 0.3565 1.0000
3.500 0.6291 0.01431 0.00631 -0.0092 0.3517 1.0000
3.750 0.6537 0.01466 0.00652 -0.0086 0.3477 1.0000
4.000 0.6784 0.01492 0.00686 -0.0081 0.3432 1.0000
4.250 0.7032 0.01518 0.00712 -0.0076 0.3387 1.0000
4.500 0.7281 0.01543 0.00730 -0.0070 0.3346 1.0000
4.750 0.7529 0.01584 0.00761 -0.0065 0.3308 1.0000
5.000 0.7776 0.01612 0.00800 -0.0060 0.3265 1.0000
5.250 0.8026 0.01643 0.00832 -0.0055 0.3224 1.0000
5.500 0.8278 0.01673 0.00857 -0.0051 0.3188 1.0000
5.750 0.8532 0.01719 0.00891 -0.0047 0.3154 1.0000
6.000 0.8779 0.01752 0.00940 -0.0043 0.3113 1.0000
6.250 0.9029 0.01787 0.00980 -0.0040 0.3073 1.0000
6.500 0.9285 0.01821 0.01012 -0.0037 0.3039 1.0000
6.750 0.9543 0.01860 0.01044 -0.0034 0.3008 1.0000
7.000 0.9790 0.01912 0.01103 -0.0031 0.2972 1.0000
7.250 1.0035 0.01952 0.01156 -0.0028 0.2931 1.0000
7.500 1.0287 0.01991 0.01199 -0.0025 0.2896 1.0000
7.750 1.0544 0.02029 0.01233 -0.0023 0.2866 1.0000
8.000 1.0803 0.02092 0.01289 -0.0022 0.2836 1.0000
8.250 1.1032 0.02139 0.01358 -0.0018 0.2798 1.0000
8.500 1.1271 0.02186 0.01416 -0.0015 0.2760 1.0000
8.750 1.1521 0.02228 0.01461 -0.0013 0.2729 1.0000
9.000 1.1781 0.02271 0.01499 -0.0012 0.2700 1.0000
9.250 1.2016 0.02341 0.01577 -0.0009 0.2667 1.0000
9.500 1.2230 0.02403 0.01660 -0.0005 0.2629 1.0000
9.750 1.2460 0.02456 0.01722 -0.0002 0.2595 1.0000
10.000 1.2710 0.02495 0.01762 0.0000 0.2564 1.0000
10.250 1.2974 0.02553 0.01811 0.0000 0.2534 1.0000
10.500 1.3156 0.02633 0.01918 0.0006 0.2499 1.0000
10.750 1.3351 0.02703 0.02006 0.0012 0.2462 1.0000
11.000 1.3579 0.02745 0.02053 0.0015 0.2428 1.0000
11.250 1.3840 0.02780 0.02082 0.0016 0.2398 1.0000
11.500 1.4033 0.02871 0.02186 0.0021 0.2366 1.0000
11.750 1.4171 0.02962 0.02303 0.0030 0.2327 1.0000
12.000 1.4360 0.03018 0.02369 0.0036 0.2291 1.0000
12.250 1.4610 0.03042 0.02389 0.0038 0.2260 1.0000
12.500 1.4817 0.03120 0.02470 0.0041 0.2227 1.0000
12.750 1.4868 0.03241 0.02622 0.0057 0.2190 1.0000
13.000 1.4991 0.03315 0.02709 0.0067 0.2154 1.0000
13.250 1.5216 0.03335 0.02727 0.0071 0.2121 1.0000
13.500 1.5420 0.03403 0.02795 0.0075 0.2088 1.0000
13.750 1.5296 0.03571 0.02992 0.0104 0.2058 1.0000
14.000 1.5233 0.03726 0.03163 0.0122 0.2027 1.0000
14.250 1.5351 0.03791 0.03231 0.0129 0.1994 1.0000
14.500 1.5669 0.03779 0.03207 0.0130 0.1956 1.0000
14.750 1.5375 0.04122 0.03581 0.0141 0.1932 1.0000
15.000 1.5165 0.04486 0.03966 0.0138 0.1901 1.0000
15.250 1.5193 0.04665 0.04152 0.0136 0.1866 1.0000
15.500 1.5616 0.04500 0.03970 0.0146 0.1825 1.0000
15.750 1.5168 0.05152 0.04655 0.0126 0.1801 1.0000
16.000 1.4703 0.05937 0.05465 0.0092 0.1771 1.0000
16.250 1.4699 0.06201 0.05735 0.0082 0.1734 1.0000
16.500 1.5196 0.05855 0.05373 0.0104 0.1691 1.0000
17.250 1.3926 0.08470 0.08043 -0.0027 0.1588 1.0000
17.500 0.9590 0.17663 0.17225 -0.0523 0.1235 1.0000
17.750 0.9838 0.17493 0.17060 -0.0512 0.1223 1.0000
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Polar data table (+)
Polar graphs
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