MH 80 12.72% (mh80-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 80 12.72% (mh80-il) Reynolds number: 200,000 Max Cl/Cd: 50.46 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh80-il-200000.txt Download as CSV file: xf-mh80-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3899 0.08806 0.08561 0.0082 1.0000 0.0533
-8.500 -0.4195 0.07951 0.07711 -0.0016 1.0000 0.0544
-8.250 -0.4477 0.07109 0.06862 -0.0110 0.9252 0.0545
-8.000 -0.4767 0.06746 0.06476 -0.0102 0.8637 0.0545
-7.750 -0.4739 0.06288 0.06016 -0.0085 0.8327 0.0552
-7.500 -0.4545 0.06145 0.05870 -0.0053 0.8014 0.0562
-7.250 -0.4561 0.05823 0.05537 -0.0046 0.7806 0.0570
-7.000 -0.4587 0.05426 0.05127 -0.0050 0.7629 0.0582
-6.750 -0.4616 0.04973 0.04656 -0.0056 0.7479 0.0601
-6.500 -0.5055 0.05261 0.04850 -0.0091 0.7735 0.0647
-6.250 -0.4884 0.04971 0.04562 -0.0084 0.7523 0.0658
-6.000 -0.4720 0.04752 0.04333 -0.0075 0.7331 0.0677
-5.500 -0.4507 0.03053 0.02417 -0.0027 0.7116 0.0325
-5.250 -0.4296 0.02670 0.01946 -0.0005 0.6972 0.0280
-5.000 -0.4056 0.02461 0.01706 0.0005 0.6813 0.0274
-4.750 -0.3802 0.02287 0.01499 0.0015 0.6655 0.0271
-4.500 -0.3539 0.02139 0.01323 0.0024 0.6501 0.0272
-4.250 -0.3271 0.02018 0.01176 0.0032 0.6351 0.0278
-4.000 -0.3006 0.01905 0.01047 0.0039 0.6208 0.0289
-3.750 -0.2747 0.01832 0.00971 0.0045 0.6070 0.0319
-3.500 -0.2487 0.01747 0.00872 0.0053 0.5942 0.0342
-3.250 -0.2232 0.01665 0.00791 0.0060 0.5809 0.0369
-3.000 -0.1978 0.01586 0.00707 0.0068 0.5680 0.0412
-2.750 -0.1723 0.01520 0.00639 0.0076 0.5561 0.0522
-2.500 -0.1503 0.01375 0.00552 0.0087 0.5454 0.1604
-2.250 -0.1273 0.01290 0.00525 0.0094 0.5337 0.2961
-2.000 -0.1078 0.01193 0.00503 0.0108 0.5235 0.4831
-1.750 -0.0925 0.01087 0.00508 0.0142 0.5133 0.7393
-1.500 -0.0611 0.01105 0.00547 0.0158 0.5016 0.8819
-1.250 -0.0198 0.01152 0.00574 0.0149 0.4903 0.9331
-1.000 0.0343 0.01187 0.00581 0.0108 0.4775 0.9551
-0.750 0.0905 0.01206 0.00578 0.0058 0.4641 0.9691
-0.500 0.1451 0.01218 0.00567 0.0009 0.4519 0.9815
-0.250 0.1991 0.01224 0.00546 -0.0042 0.4413 0.9924
0.000 0.2464 0.01216 0.00524 -0.0081 0.4302 1.0000
0.250 0.2703 0.01223 0.00517 -0.0075 0.4225 1.0000
0.500 0.2947 0.01226 0.00510 -0.0070 0.4143 1.0000
0.750 0.3190 0.01237 0.00507 -0.0064 0.4076 1.0000
1.000 0.3437 0.01243 0.00508 -0.0059 0.4001 1.0000
1.250 0.3682 0.01256 0.00506 -0.0053 0.3939 1.0000
1.500 0.3929 0.01267 0.00513 -0.0048 0.3868 1.0000
1.750 0.4174 0.01278 0.00515 -0.0042 0.3803 1.0000
2.000 0.4418 0.01298 0.00524 -0.0036 0.3749 1.0000
2.250 0.4665 0.01312 0.00538 -0.0031 0.3687 1.0000
2.500 0.4910 0.01328 0.00546 -0.0024 0.3634 1.0000
2.750 0.5153 0.01353 0.00562 -0.0018 0.3582 1.0000
3.000 0.5398 0.01369 0.00579 -0.0012 0.3523 1.0000
3.250 0.5641 0.01388 0.00591 -0.0006 0.3475 1.0000
3.500 0.5883 0.01420 0.00614 0.0000 0.3433 1.0000
3.750 0.6127 0.01440 0.00640 0.0006 0.3381 1.0000
4.000 0.6369 0.01461 0.00658 0.0013 0.3332 1.0000
4.250 0.6609 0.01490 0.00676 0.0020 0.3291 1.0000
4.500 0.6850 0.01521 0.00712 0.0026 0.3248 1.0000
4.750 0.7090 0.01548 0.00743 0.0032 0.3203 1.0000
5.000 0.7330 0.01574 0.00765 0.0039 0.3162 1.0000
5.250 0.7570 0.01612 0.00791 0.0045 0.3124 1.0000
5.500 0.7806 0.01643 0.00835 0.0052 0.3081 1.0000
5.750 0.8045 0.01674 0.00871 0.0058 0.3039 1.0000
6.000 0.8286 0.01704 0.00898 0.0064 0.3003 1.0000
6.250 0.8528 0.01748 0.00932 0.0070 0.2969 1.0000
6.500 0.8761 0.01786 0.00985 0.0076 0.2928 1.0000
6.750 0.8996 0.01820 0.01026 0.0082 0.2886 1.0000
7.000 0.9237 0.01854 0.01060 0.0088 0.2851 1.0000
7.250 0.9482 0.01897 0.01096 0.0093 0.2821 1.0000
7.500 0.9714 0.01951 0.01160 0.0098 0.2785 1.0000
7.750 0.9946 0.01992 0.01215 0.0104 0.2742 1.0000
8.000 1.0187 0.02028 0.01253 0.0108 0.2705 1.0000
8.250 1.0436 0.02068 0.01289 0.0112 0.2675 1.0000
8.500 1.0674 0.02134 0.01359 0.0116 0.2643 1.0000
8.750 1.0895 0.02186 0.01431 0.0121 0.2602 1.0000
9.000 1.1131 0.02228 0.01481 0.0125 0.2564 1.0000
9.250 1.1379 0.02266 0.01518 0.0128 0.2532 1.0000
9.500 1.1630 0.02336 0.01581 0.0130 0.2501 1.0000
9.750 1.1830 0.02397 0.01670 0.0135 0.2463 1.0000
10.000 1.2049 0.02450 0.01737 0.0140 0.2423 1.0000
10.250 1.2292 0.02488 0.01776 0.0143 0.2390 1.0000
10.500 1.2550 0.02541 0.01819 0.0144 0.2358 1.0000
10.750 1.2727 0.02622 0.01929 0.0151 0.2320 1.0000
11.000 1.2922 0.02687 0.02011 0.0156 0.2280 1.0000
11.250 1.3155 0.02721 0.02048 0.0160 0.2245 1.0000
11.500 1.3417 0.02766 0.02083 0.0161 0.2213 1.0000
11.750 1.3553 0.02864 0.02211 0.0170 0.2175 1.0000
12.000 1.3717 0.02934 0.02298 0.0177 0.2134 1.0000
12.250 1.3938 0.02965 0.02331 0.0182 0.2099 1.0000
12.500 1.4194 0.03014 0.02371 0.0182 0.2064 1.0000
12.750 1.4246 0.03132 0.02524 0.0197 0.2026 1.0000
13.000 1.4370 0.03206 0.02612 0.0207 0.1987 1.0000
13.250 1.4585 0.03228 0.02631 0.0212 0.1951 1.0000
13.500 1.4727 0.03315 0.02725 0.0220 0.1915 1.0000
13.750 1.4649 0.03465 0.02900 0.0244 0.1882 1.0000
14.000 1.4652 0.03582 0.03029 0.0258 0.1848 1.0000
14.250 1.4829 0.03612 0.03054 0.0264 0.1811 1.0000
14.500 1.4838 0.03777 0.03229 0.0271 0.1779 1.0000
14.750 1.4652 0.04092 0.03569 0.0271 0.1748 1.0000
15.000 1.4610 0.04326 0.03814 0.0268 0.1712 1.0000
15.250 1.4831 0.04329 0.03807 0.0272 0.1672 1.0000
15.500 1.4649 0.04732 0.04232 0.0259 0.1641 1.0000
15.750 1.4381 0.05269 0.04790 0.0236 0.1610 1.0000
16.000 1.4367 0.05536 0.05063 0.0225 0.1571 1.0000
16.250 1.4549 0.05572 0.05091 0.0228 0.1527 1.0000
16.500 1.4084 0.06433 0.05981 0.0184 0.1502 1.0000
16.750 1.3550 0.07480 0.07050 0.0128 0.1473 1.0000
17.000 1.4266 0.06731 0.06273 0.0174 0.1412 1.0000
17.250 1.3665 0.07918 0.07490 0.0108 0.1391 1.0000
17.500 0.6932 0.17222 0.16846 -0.0383 0.1180 1.0000
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Polar data table (+)
Polar graphs
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