MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 25 9.98% (mh25-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.01 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh25-il-1000000.txt Download as CSV file: xf-mh25-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 25 9.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3441 0.08375 0.08220 -0.0533 0.9919 0.0068
-10.000 -0.3460 0.07875 0.07721 -0.0554 0.9911 0.0068
-9.750 -0.4418 0.08405 0.08244 -0.0522 0.9937 0.0062
-9.500 -0.4468 0.07762 0.07604 -0.0572 0.9917 0.0063
-9.250 -0.4448 0.07112 0.06955 -0.0644 0.9898 0.0062
-9.000 -0.4456 0.06369 0.06205 -0.0732 0.9875 0.0062
-8.750 -0.4463 0.05828 0.05653 -0.0771 0.9855 0.0061
-8.500 -0.4556 0.05157 0.04965 -0.0797 0.9831 0.0063
-8.250 -0.4578 0.04733 0.04525 -0.0793 0.9801 0.0064
-8.000 -0.4600 0.04358 0.04134 -0.0776 0.9766 0.0065
-7.750 -0.4530 0.04013 0.03771 -0.0771 0.9744 0.0067
-7.500 -0.4423 0.03714 0.03453 -0.0765 0.9727 0.0070
-7.250 -0.4286 0.03429 0.03148 -0.0759 0.9713 0.0071
-7.000 -0.4133 0.03174 0.02873 -0.0752 0.9697 0.0075
-6.750 -0.4096 0.03003 0.02686 -0.0712 0.9656 0.0078
-6.500 -0.3979 0.02784 0.02446 -0.0687 0.9626 0.0083
-4.500 -0.2318 0.01328 0.00805 -0.0561 0.9460 0.0061
-4.250 -0.2102 0.01156 0.00621 -0.0545 0.9442 0.0052
-4.000 -0.1907 0.01079 0.00533 -0.0526 0.9414 0.0049
-3.750 -0.1715 0.01021 0.00464 -0.0506 0.9377 0.0047
-3.500 -0.1477 0.00976 0.00410 -0.0497 0.9350 0.0047
-3.250 -0.1222 0.00936 0.00362 -0.0490 0.9329 0.0049
-3.000 -0.0954 0.00908 0.00325 -0.0486 0.9309 0.0054
-2.750 -0.0736 0.00862 0.00293 -0.0473 0.9279 0.0487
-2.500 -0.0549 0.00804 0.00274 -0.0456 0.9237 0.1508
-2.250 -0.0368 0.00726 0.00251 -0.0439 0.9204 0.3065
-2.000 -0.0188 0.00648 0.00230 -0.0421 0.9176 0.4724
-1.750 -0.0138 0.00552 0.00216 -0.0374 0.9125 0.6982
-1.500 -0.0008 0.00504 0.00226 -0.0336 0.9081 0.8653
-1.250 0.0265 0.00499 0.00219 -0.0332 0.9054 0.8862
-1.000 0.0550 0.00497 0.00215 -0.0331 0.9028 0.8988
-0.750 0.0793 0.00499 0.00217 -0.0322 0.8977 0.9074
-0.500 0.1051 0.00496 0.00210 -0.0316 0.8934 0.9156
-0.250 0.1354 0.00497 0.00210 -0.0318 0.8901 0.9211
0.000 0.1578 0.00503 0.00216 -0.0304 0.8839 0.9295
0.250 0.1884 0.00511 0.00223 -0.0307 0.8788 0.9341
0.500 0.2148 0.00515 0.00227 -0.0302 0.8723 0.9389
0.750 0.2396 0.00512 0.00221 -0.0294 0.8641 0.9431
1.000 0.2699 0.00516 0.00225 -0.0298 0.8536 0.9452
1.250 0.3014 0.00522 0.00228 -0.0305 0.8403 0.9476
1.500 0.3329 0.00530 0.00231 -0.0312 0.8212 0.9505
1.750 0.3524 0.00540 0.00231 -0.0292 0.7930 0.9562
2.000 0.3852 0.00561 0.00236 -0.0302 0.7559 0.9576
2.250 0.4162 0.00586 0.00244 -0.0310 0.7148 0.9589
2.500 0.4450 0.00614 0.00254 -0.0313 0.6668 0.9602
2.750 0.4714 0.00641 0.00266 -0.0312 0.6224 0.9619
3.000 0.4947 0.00669 0.00276 -0.0305 0.5759 0.9641
3.250 0.5011 0.00691 0.00284 -0.0259 0.5375 0.9697
3.500 0.5294 0.00723 0.00295 -0.0264 0.4838 0.9705
3.750 0.5575 0.00754 0.00309 -0.0268 0.4341 0.9713
4.000 0.5854 0.00783 0.00322 -0.0272 0.3906 0.9722
4.250 0.6122 0.00818 0.00338 -0.0275 0.3416 0.9733
4.500 0.6383 0.00851 0.00354 -0.0275 0.2991 0.9746
4.750 0.6632 0.00887 0.00373 -0.0273 0.2551 0.9762
5.000 0.6853 0.00927 0.00393 -0.0266 0.2091 0.9782
5.250 0.7019 0.00965 0.00416 -0.0245 0.1695 0.9809
5.500 0.7240 0.00998 0.00437 -0.0237 0.1392 0.9827
5.750 0.7524 0.01034 0.00461 -0.0243 0.1109 0.9834
6.000 0.7801 0.01071 0.00487 -0.0248 0.0866 0.9842
6.250 0.8070 0.01111 0.00517 -0.0251 0.0644 0.9851
6.500 0.8334 0.01153 0.00551 -0.0253 0.0452 0.9861
6.750 0.8588 0.01200 0.00589 -0.0253 0.0281 0.9873
7.000 0.8840 0.01246 0.00635 -0.0252 0.0192 0.9887
7.250 0.9101 0.01279 0.00670 -0.0253 0.0163 0.9901
7.500 0.9330 0.01337 0.00732 -0.0247 0.0124 0.9918
7.750 0.9564 0.01368 0.00768 -0.0242 0.0115 0.9934
8.000 0.9819 0.01407 0.00801 -0.0243 0.0061 0.9944
8.250 1.0071 0.01478 0.00876 -0.0244 0.0037 0.9954
8.500 1.0319 0.01546 0.00953 -0.0243 0.0031 0.9965
8.750 1.0568 0.01607 0.01023 -0.0243 0.0027 0.9977
9.000 1.0818 0.01663 0.01086 -0.0244 0.0024 0.9989
9.250 1.1035 0.01758 0.01197 -0.0238 0.0023 1.0000
9.500 1.1090 0.01803 0.01249 -0.0197 0.0022 1.0000
9.750 1.1079 0.01836 0.01288 -0.0143 0.0021 1.0000
10.000 1.1006 0.01881 0.01342 -0.0076 0.0021 1.0000
10.250 1.0958 0.01943 0.01415 -0.0015 0.0020 1.0000
10.500 1.0998 0.02000 0.01479 0.0026 0.0020 1.0000
10.750 1.1051 0.02078 0.01566 0.0062 0.0018 1.0000
11.000 1.1097 0.02176 0.01675 0.0097 0.0017 1.0000
11.250 1.1128 0.02296 0.01811 0.0134 0.0018 1.0000
11.500 1.1099 0.02470 0.02003 0.0176 0.0016 1.0000
11.750 1.1081 0.02644 0.02197 0.0214 0.0015 1.0000
12.000 1.1019 0.02861 0.02435 0.0254 0.0015 1.0000
12.250 1.0802 0.03225 0.02835 0.0306 0.0014 1.0000
12.500 1.0911 0.03295 0.02910 0.0320 0.0014 1.0000
12.750 1.0966 0.03420 0.03046 0.0338 0.0014 1.0000
13.000 1.1006 0.03562 0.03197 0.0354 0.0013 1.0000
13.250 1.0755 0.03997 0.03662 0.0385 0.0014 1.0000
13.500 1.0873 0.04081 0.03752 0.0389 0.0013 1.0000
13.750 1.0893 0.04279 0.03958 0.0396 0.0011 1.0000
14.000 1.0717 0.04715 0.04416 0.0400 0.0012 1.0000
14.250 1.0136 0.05788 0.05528 0.0374 0.0014 1.0000
14.500 1.0477 0.05607 0.05338 0.0379 0.0011 1.0000
14.750 1.0004 0.06743 0.06505 0.0323 0.0013 1.0000
15.000 0.9685 0.07778 0.07558 0.0263 0.0013 1.0000
15.250 0.9594 0.08419 0.08208 0.0225 0.0013 1.0000
15.500 0.9590 0.08881 0.08677 0.0198 0.0012 1.0000
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Polar data table (+)
Polar graphs
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