MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 80 12.72% (mh80-il) Reynolds number: 50,000 Max Cl/Cd: 22.65 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh80-il-50000-n5.txt Download as CSV file: xf-mh80-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 80 12.72%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4718 0.09657 0.09069 0.0063 1.0000 0.0444
-8.750 -0.4718 0.09168 0.08587 0.0032 1.0000 0.0435
-8.500 -0.4743 0.08617 0.08045 -0.0010 1.0000 0.0426
-8.250 -0.4843 0.07913 0.07348 -0.0074 1.0000 0.0413
-8.000 -0.5112 0.07070 0.06487 -0.0132 1.0000 0.0394
-7.750 -0.5118 0.06645 0.06056 -0.0147 1.0000 0.0391
-7.500 -0.5112 0.06213 0.05613 -0.0159 1.0000 0.0389
-7.250 -0.5080 0.05788 0.05170 -0.0168 1.0000 0.0386
-7.000 -0.5025 0.05361 0.04718 -0.0175 1.0000 0.0385
-6.750 -0.4934 0.04964 0.04291 -0.0179 1.0000 0.0384
-6.500 -0.4824 0.04573 0.03857 -0.0181 1.0000 0.0389
-6.250 -0.4546 0.04190 0.03415 -0.0204 0.9208 0.0399
-6.000 -0.4287 0.03983 0.03185 -0.0210 0.8795 0.0418
-5.750 -0.4091 0.03765 0.02920 -0.0198 0.8479 0.0433
-5.500 -0.3897 0.03553 0.02657 -0.0181 0.8208 0.0446
-5.250 -0.3690 0.03354 0.02403 -0.0161 0.7978 0.0458
-5.000 -0.3469 0.03189 0.02210 -0.0146 0.7755 0.0476
-4.750 -0.3246 0.03069 0.02070 -0.0132 0.7548 0.0510
-4.500 -0.3005 0.02938 0.01907 -0.0117 0.7359 0.0553
-4.250 -0.2767 0.02825 0.01781 -0.0104 0.7178 0.0600
-4.000 -0.2521 0.02719 0.01660 -0.0092 0.7006 0.0674
-3.750 -0.2271 0.02619 0.01549 -0.0081 0.6840 0.0789
-3.500 -0.2017 0.02523 0.01441 -0.0071 0.6680 0.0996
-3.250 -0.1773 0.02406 0.01349 -0.0063 0.6528 0.1449
-3.000 -0.1558 0.02278 0.01273 -0.0053 0.6386 0.2406
-2.750 -0.1387 0.02157 0.01227 -0.0035 0.6256 0.3844
-2.500 -0.1219 0.02031 0.01223 0.0003 0.6134 0.6274
-2.250 -0.0649 0.02053 0.01260 -0.0007 0.5965 0.8460
-2.000 -0.0202 0.02090 0.01253 -0.0021 0.5811 0.9127
-1.750 0.0395 0.02106 0.01218 -0.0070 0.5647 0.9576
-1.500 0.1120 0.02089 0.01148 -0.0151 0.5476 0.9947
-1.250 0.1423 0.02088 0.01117 -0.0160 0.5354 1.0000
-1.000 0.1639 0.02093 0.01092 -0.0151 0.5255 1.0000
-0.750 0.1866 0.02105 0.01084 -0.0145 0.5143 1.0000
-0.500 0.2091 0.02120 0.01078 -0.0138 0.5046 1.0000
-0.250 0.2315 0.02135 0.01070 -0.0129 0.4952 1.0000
0.000 0.2546 0.02158 0.01077 -0.0123 0.4853 1.0000
0.250 0.2770 0.02176 0.01073 -0.0114 0.4773 1.0000
0.500 0.3005 0.02207 0.01093 -0.0109 0.4677 1.0000
0.750 0.3230 0.02229 0.01094 -0.0099 0.4604 1.0000
1.000 0.3463 0.02267 0.01124 -0.0095 0.4514 1.0000
1.250 0.3690 0.02294 0.01133 -0.0086 0.4444 1.0000
1.500 0.3922 0.02337 0.01170 -0.0080 0.4364 1.0000
1.750 0.4150 0.02372 0.01192 -0.0072 0.4293 1.0000
2.000 0.4378 0.02413 0.01223 -0.0065 0.4227 1.0000
2.250 0.4606 0.02462 0.01268 -0.0059 0.4151 1.0000
2.500 0.4833 0.02495 0.01284 -0.0049 0.4100 1.0000
2.750 0.5058 0.02563 0.01357 -0.0046 0.4024 1.0000
3.000 0.5284 0.02608 0.01395 -0.0038 0.3964 1.0000
3.250 0.5509 0.02653 0.01430 -0.0029 0.3913 1.0000
3.500 0.5726 0.02735 0.01520 -0.0026 0.3843 1.0000
3.750 0.5949 0.02783 0.01562 -0.0017 0.3792 1.0000
4.000 0.6169 0.02845 0.01620 -0.0010 0.3741 1.0000
4.250 0.6373 0.02939 0.01723 -0.0006 0.3675 1.0000
4.500 0.6594 0.02991 0.01770 0.0003 0.3629 1.0000
4.750 0.6811 0.03058 0.01835 0.0010 0.3585 1.0000
5.000 0.6993 0.03186 0.01979 0.0013 0.3521 1.0000
5.250 0.7208 0.03251 0.02042 0.0021 0.3475 1.0000
5.500 0.7444 0.03287 0.02067 0.0031 0.3441 1.0000
5.750 0.7578 0.03480 0.02290 0.0031 0.3373 1.0000
6.000 0.7769 0.03581 0.02396 0.0038 0.3327 1.0000
6.250 0.8000 0.03625 0.02435 0.0046 0.3292 1.0000
6.500 0.8113 0.03830 0.02659 0.0048 0.3234 1.0000
6.750 0.8240 0.04005 0.02850 0.0052 0.3181 1.0000
7.000 0.8447 0.04081 0.02927 0.0059 0.3146 1.0000
7.250 0.8658 0.04157 0.03002 0.0067 0.3114 1.0000
7.500 0.8504 0.04639 0.03519 0.0061 0.3036 1.0000
7.750 0.8657 0.04764 0.03650 0.0067 0.2997 1.0000
8.000 0.8916 0.04779 0.03664 0.0077 0.2971 1.0000
8.250 0.7951 0.06143 0.05052 0.0028 0.2853 1.0000
8.500 0.8177 0.06161 0.05074 0.0041 0.2827 1.0000
8.750 0.8506 0.06065 0.04980 0.0060 0.2810 1.0000
9.750 0.7453 0.08887 0.07811 -0.0064 0.2537 1.0000
10.000 0.7636 0.09000 0.07928 -0.0058 0.2513 1.0000
10.250 0.7383 0.09725 0.08656 -0.0093 0.2456 1.0000
10.500 0.7372 0.10104 0.09039 -0.0105 0.2409 1.0000
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Polar data table (+)
Polar graphs
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