MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 25 9.98% (mh25-il) Reynolds number: 500,000 Max Cl/Cd: 60.56 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh25-il-500000-n5.txt Download as CSV file: xf-mh25-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4353 0.08369 0.08141 -0.0532 0.9884 0.0080
-9.250 -0.4340 0.07825 0.07599 -0.0581 0.9867 0.0079
-9.000 -0.4363 0.07068 0.06842 -0.0674 0.9846 0.0078
-8.750 -0.4389 0.06385 0.06151 -0.0750 0.9825 0.0077
-8.500 -0.4494 0.05913 0.05669 -0.0761 0.9778 0.0077
-8.250 -0.4511 0.05434 0.05176 -0.0772 0.9745 0.0077
-8.000 -0.4517 0.04826 0.04544 -0.0778 0.9718 0.0073
-7.750 -0.4405 0.04291 0.03984 -0.0774 0.9700 0.0053
-7.500 -0.4477 0.03900 0.03568 -0.0736 0.9652 0.0050
-7.250 -0.4441 0.03532 0.03172 -0.0710 0.9616 0.0047
-7.000 -0.4388 0.03092 0.02693 -0.0681 0.9589 0.0043
-6.750 -0.4284 0.02666 0.02219 -0.0654 0.9569 0.0039
-6.500 -0.4261 0.02226 0.01716 -0.0599 0.9526 0.0034
-6.250 -0.4093 0.02032 0.01488 -0.0577 0.9498 0.0033
-6.000 -0.3877 0.01894 0.01324 -0.0565 0.9480 0.0032
-5.750 -0.3642 0.01759 0.01167 -0.0557 0.9465 0.0031
-5.500 -0.3395 0.01640 0.01029 -0.0551 0.9452 0.0031
-5.250 -0.3141 0.01544 0.00919 -0.0547 0.9441 0.0031
-5.000 -0.2890 0.01461 0.00825 -0.0543 0.9428 0.0031
-4.750 -0.2750 0.01386 0.00737 -0.0514 0.9387 0.0031
-4.500 -0.2544 0.01316 0.00658 -0.0499 0.9360 0.0031
-4.250 -0.2313 0.01249 0.00582 -0.0490 0.9338 0.0033
-4.000 -0.2059 0.01196 0.00520 -0.0485 0.9320 0.0034
-3.750 -0.1793 0.01151 0.00465 -0.0482 0.9305 0.0037
-3.500 -0.1578 0.01126 0.00434 -0.0469 0.9271 0.0040
-3.250 -0.1358 0.01100 0.00402 -0.0456 0.9234 0.0053
-3.000 -0.1107 0.01066 0.00370 -0.0450 0.9207 0.0172
-2.750 -0.0870 0.01005 0.00340 -0.0444 0.9183 0.0894
-2.500 -0.0666 0.00919 0.00314 -0.0433 0.9159 0.2393
-2.250 -0.0550 0.00853 0.00302 -0.0403 0.9098 0.3840
-2.000 -0.0391 0.00777 0.00281 -0.0380 0.9059 0.5347
-1.750 -0.0215 0.00709 0.00258 -0.0358 0.9031 0.6639
-1.500 -0.0090 0.00667 0.00262 -0.0322 0.8967 0.7790
-1.250 0.0206 0.00662 0.00276 -0.0321 0.8934 0.8535
-1.000 0.0498 0.00659 0.00270 -0.0321 0.8904 0.8758
-0.750 0.0731 0.00664 0.00274 -0.0309 0.8842 0.8913
-0.500 0.1001 0.00668 0.00276 -0.0304 0.8791 0.9058
-0.250 0.1245 0.00673 0.00279 -0.0294 0.8729 0.9167
0.000 0.1535 0.00677 0.00282 -0.0294 0.8657 0.9222
0.250 0.1743 0.00676 0.00278 -0.0278 0.8563 0.9291
0.500 0.2077 0.00678 0.00279 -0.0288 0.8472 0.9322
0.750 0.2398 0.00682 0.00279 -0.0295 0.8350 0.9366
1.000 0.2642 0.00681 0.00274 -0.0286 0.8176 0.9428
1.250 0.3017 0.00684 0.00267 -0.0305 0.7938 0.9444
1.500 0.3350 0.00693 0.00263 -0.0316 0.7621 0.9459
1.750 0.3635 0.00710 0.00262 -0.0317 0.7239 0.9478
2.000 0.3873 0.00732 0.00266 -0.0309 0.6829 0.9503
2.250 0.3977 0.00751 0.00269 -0.0271 0.6450 0.9560
2.500 0.4240 0.00778 0.00278 -0.0270 0.6011 0.9572
2.750 0.4494 0.00808 0.00291 -0.0267 0.5560 0.9586
3.000 0.4744 0.00839 0.00304 -0.0264 0.5107 0.9601
3.250 0.4989 0.00868 0.00317 -0.0260 0.4679 0.9619
3.500 0.5213 0.00898 0.00331 -0.0251 0.4254 0.9641
3.750 0.5391 0.00926 0.00344 -0.0233 0.3872 0.9675
4.000 0.5579 0.00955 0.00360 -0.0217 0.3477 0.9700
4.250 0.5847 0.00989 0.00379 -0.0219 0.3069 0.9709
4.500 0.6116 0.01024 0.00400 -0.0222 0.2679 0.9719
4.750 0.6380 0.01060 0.00422 -0.0223 0.2310 0.9732
5.000 0.6633 0.01097 0.00446 -0.0223 0.1975 0.9746
5.250 0.6873 0.01135 0.00475 -0.0219 0.1635 0.9762
5.500 0.7099 0.01177 0.00503 -0.0213 0.1313 0.9781
5.750 0.7303 0.01219 0.00533 -0.0202 0.1014 0.9807
6.000 0.7526 0.01260 0.00564 -0.0195 0.0790 0.9826
6.250 0.7794 0.01302 0.00600 -0.0198 0.0595 0.9835
6.500 0.8057 0.01345 0.00639 -0.0200 0.0447 0.9846
6.750 0.8315 0.01389 0.00680 -0.0201 0.0336 0.9858
7.000 0.8568 0.01432 0.00725 -0.0201 0.0258 0.9872
7.250 0.8809 0.01485 0.00782 -0.0198 0.0198 0.9888
7.500 0.9055 0.01525 0.00829 -0.0196 0.0170 0.9905
7.750 0.9284 0.01580 0.00884 -0.0192 0.0129 0.9925
8.000 0.9524 0.01621 0.00929 -0.0189 0.0101 0.9942
8.250 0.9774 0.01673 0.00986 -0.0190 0.0082 0.9955
8.500 1.0005 0.01743 0.01063 -0.0187 0.0064 0.9972
8.750 1.0244 0.01799 0.01125 -0.0186 0.0044 0.9988
9.000 1.0414 0.01878 0.01212 -0.0170 0.0035 1.0000
9.250 1.0400 0.01940 0.01285 -0.0115 0.0029 1.0000
9.500 1.0408 0.01990 0.01345 -0.0065 0.0028 1.0000
9.750 1.0432 0.02051 0.01420 -0.0020 0.0027 1.0000
10.000 1.0468 0.02127 0.01508 0.0022 0.0026 1.0000
10.250 1.0514 0.02215 0.01609 0.0060 0.0023 1.0000
10.500 1.0589 0.02294 0.01698 0.0090 0.0023 1.0000
10.750 1.0685 0.02369 0.01782 0.0116 0.0020 1.0000
11.000 1.0803 0.02433 0.01852 0.0137 0.0018 1.0000
11.250 1.0836 0.02566 0.02002 0.0171 0.0018 1.0000
11.500 1.0858 0.02711 0.02161 0.0201 0.0015 1.0000
11.750 1.0888 0.02853 0.02318 0.0230 0.0014 1.0000
12.000 1.0906 0.03009 0.02491 0.0259 0.0014 1.0000
12.250 1.0933 0.03161 0.02660 0.0283 0.0013 1.0000
12.500 1.0960 0.03314 0.02829 0.0306 0.0013 1.0000
12.750 1.0951 0.03506 0.03038 0.0329 0.0013 1.0000
13.000 1.0932 0.03712 0.03262 0.0349 0.0013 1.0000
13.250 1.0828 0.04013 0.03584 0.0369 0.0013 1.0000
13.500 1.0801 0.04254 0.03844 0.0380 0.0012 1.0000
13.750 1.0734 0.04557 0.04165 0.0387 0.0012 1.0000
14.000 1.0608 0.04957 0.04585 0.0387 0.0012 1.0000
14.250 1.0401 0.05514 0.05163 0.0376 0.0012 1.0000
14.500 1.0348 0.05910 0.05574 0.0360 0.0012 1.0000
14.750 1.0085 0.06699 0.06385 0.0322 0.0012 1.0000
15.000 0.9879 0.07482 0.07186 0.0277 0.0012 1.0000
15.250 0.9715 0.08248 0.07966 0.0233 0.0012 1.0000
15.500 0.9554 0.09040 0.08770 0.0188 0.0012 1.0000
15.750 0.9254 0.10164 0.09905 0.0127 0.0013 1.0000
16.000 0.9010 0.11179 0.10930 0.0076 0.0013 1.0000
16.250 0.8805 0.12132 0.11891 0.0029 0.0013 1.0000
16.500 0.8535 0.13264 0.13030 -0.0024 0.0013 1.0000
16.750 0.8257 0.14481 0.14252 -0.0080 0.0014 1.0000
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Polar data table (+)
Polar graphs
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