MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: MH 25 9.98% (mh25-il) Reynolds number: 100,000 Max Cl/Cd: 47.96 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh25-il-100000-n5.txt Download as CSV file: xf-mh25-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4860 0.09215 0.08726 -0.0363 1.0000 0.0166
-9.000 -0.4956 0.08832 0.08350 -0.0369 1.0000 0.0163
-8.750 -0.5074 0.08443 0.07967 -0.0378 1.0000 0.0160
-8.500 -0.5248 0.08026 0.07556 -0.0388 1.0000 0.0158
-8.250 -0.5435 0.07722 0.07254 -0.0375 1.0000 0.0156
-8.000 -0.5650 0.07457 0.06989 -0.0344 1.0000 0.0155
-7.750 -0.5810 0.07129 0.06658 -0.0319 1.0000 0.0152
-7.500 -0.5950 0.06767 0.06289 -0.0292 1.0000 0.0149
-7.250 -0.6053 0.06413 0.05924 -0.0265 1.0000 0.0145
-7.000 -0.6145 0.06015 0.05509 -0.0235 1.0000 0.0141
-6.750 -0.6204 0.05600 0.05071 -0.0203 1.0000 0.0135
-6.500 -0.6246 0.05131 0.04567 -0.0166 1.0000 0.0129
-6.250 -0.6229 0.04756 0.04156 -0.0132 1.0000 0.0124
-6.000 -0.6172 0.04455 0.03820 -0.0100 1.0000 0.0120
-5.750 -0.6098 0.04175 0.03503 -0.0070 1.0000 0.0119
-5.500 -0.6003 0.03918 0.03209 -0.0042 1.0000 0.0118
-5.000 -0.5638 0.03403 0.02604 -0.0016 0.9966 0.0115
-4.500 -0.5144 0.02885 0.01993 -0.0005 0.9917 0.0118
-4.250 -0.4882 0.02661 0.01734 -0.0002 0.9891 0.0122
-4.000 -0.4608 0.02507 0.01562 -0.0003 0.9864 0.0136
-3.750 -0.4309 0.02420 0.01457 -0.0010 0.9837 0.0173
-3.500 -0.4021 0.02313 0.01326 -0.0011 0.9809 0.0191
-3.250 -0.3777 0.02186 0.01184 -0.0003 0.9771 0.0215
-3.000 -0.3502 0.02100 0.01087 -0.0003 0.9734 0.0268
-2.750 -0.3209 0.02006 0.00999 -0.0006 0.9703 0.0532
-2.500 -0.3014 0.01829 0.00947 0.0002 0.9664 0.2663
-2.000 -0.1866 0.01802 0.01122 -0.0080 0.9718 0.9433
-1.750 -0.1097 0.01855 0.01138 -0.0177 0.9751 0.9727
-1.500 -0.0243 0.01876 0.01126 -0.0298 0.9806 0.9969
-1.250 0.0141 0.01873 0.01104 -0.0326 0.9764 1.0000
-1.000 0.0492 0.01876 0.01093 -0.0348 0.9714 1.0000
-0.750 0.0806 0.01875 0.01081 -0.0361 0.9651 1.0000
-0.500 0.1150 0.01875 0.01070 -0.0380 0.9592 1.0000
-0.250 0.1476 0.01874 0.01062 -0.0395 0.9527 1.0000
0.000 0.1818 0.01871 0.01053 -0.0412 0.9459 1.0000
0.250 0.2132 0.01866 0.01046 -0.0424 0.9386 1.0000
0.500 0.2499 0.01859 0.01037 -0.0445 0.9317 1.0000
0.750 0.2787 0.01850 0.01027 -0.0449 0.9226 1.0000
1.000 0.3204 0.01835 0.01014 -0.0479 0.9168 1.0000
1.250 0.3467 0.01820 0.01002 -0.0478 0.9058 1.0000
1.750 0.4071 0.01778 0.00972 -0.0487 0.8848 1.0000
2.000 0.4409 0.01748 0.00949 -0.0498 0.8745 1.0000
2.250 0.4643 0.01722 0.00930 -0.0487 0.8602 1.0000
2.500 0.4853 0.01696 0.00917 -0.0471 0.8439 1.0000
2.750 0.5093 0.01665 0.00894 -0.0460 0.8270 1.0000
3.000 0.5368 0.01632 0.00871 -0.0455 0.8082 1.0000
3.250 0.5678 0.01595 0.00844 -0.0456 0.7854 1.0000
3.500 0.6071 0.01548 0.00810 -0.0472 0.7568 1.0000
3.750 0.6525 0.01503 0.00765 -0.0499 0.7131 1.0000
4.000 0.6932 0.01484 0.00733 -0.0517 0.6518 1.0000
4.250 0.7209 0.01503 0.00732 -0.0512 0.5862 1.0000
4.500 0.7404 0.01544 0.00748 -0.0493 0.5224 1.0000
4.750 0.7557 0.01595 0.00782 -0.0468 0.4620 1.0000
5.000 0.7692 0.01652 0.00818 -0.0441 0.4055 1.0000
5.250 0.7816 0.01713 0.00859 -0.0413 0.3518 1.0000
5.500 0.7937 0.01777 0.00904 -0.0384 0.3023 1.0000
5.750 0.8052 0.01845 0.00954 -0.0355 0.2546 1.0000
6.000 0.8164 0.01916 0.01008 -0.0327 0.2109 1.0000
6.250 0.8276 0.01991 0.01067 -0.0298 0.1707 1.0000
6.500 0.8386 0.02070 0.01132 -0.0270 0.1344 1.0000
6.750 0.8490 0.02154 0.01205 -0.0241 0.1059 1.0000
7.000 0.8590 0.02242 0.01284 -0.0211 0.0817 1.0000
7.250 0.8679 0.02336 0.01376 -0.0178 0.0671 1.0000
7.500 0.8764 0.02433 0.01487 -0.0144 0.0564 1.0000
7.750 0.8845 0.02532 0.01592 -0.0110 0.0477 1.0000
8.000 0.8906 0.02643 0.01700 -0.0075 0.0413 1.0000
8.250 0.8994 0.02753 0.01832 -0.0042 0.0374 1.0000
8.500 0.9076 0.02878 0.01970 -0.0009 0.0339 1.0000
8.750 0.9142 0.03019 0.02116 0.0024 0.0310 1.0000
9.000 0.9247 0.03174 0.02292 0.0052 0.0274 1.0000
9.250 0.9350 0.03326 0.02466 0.0080 0.0242 1.0000
9.500 0.9430 0.03493 0.02648 0.0108 0.0221 1.0000
9.750 0.9473 0.03738 0.02904 0.0137 0.0197 1.0000
10.000 0.9527 0.03896 0.03100 0.0169 0.0176 1.0000
10.250 0.9549 0.04153 0.03392 0.0203 0.0160 1.0000
10.500 0.9542 0.04403 0.03673 0.0236 0.0155 1.0000
10.750 0.9489 0.04662 0.03962 0.0272 0.0148 1.0000
11.000 0.9422 0.04895 0.04219 0.0304 0.0141 1.0000
11.250 0.9337 0.05140 0.04485 0.0331 0.0135 1.0000
11.500 0.9230 0.05422 0.04789 0.0355 0.0132 1.0000
11.750 0.9101 0.05746 0.05135 0.0373 0.0130 1.0000
12.000 0.8951 0.06080 0.05485 0.0381 0.0122 1.0000
12.250 0.8730 0.06572 0.05990 0.0380 0.0119 1.0000
12.500 0.8611 0.06988 0.06429 0.0371 0.0123 1.0000
12.750 0.8421 0.07565 0.07028 0.0346 0.0124 1.0000
13.000 0.7995 0.08812 0.08315 0.0272 0.0144 1.0000
13.250 0.7669 0.10066 0.09581 0.0190 0.0154 1.0000
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Polar data table (+)
Polar graphs
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