MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 25 9.98% (mh25-il) Reynolds number: 200,000 Max Cl/Cd: 70.87 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh25-il-200000.txt Download as CSV file: xf-mh25-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5070 0.08880 0.08551 -0.0326 1.0000 0.0351
-8.500 -0.5211 0.08512 0.08190 -0.0332 1.0000 0.0354
-8.250 -0.5403 0.08163 0.07844 -0.0337 1.0000 0.0351
-8.000 -0.5637 0.07899 0.07580 -0.0314 1.0000 0.0350
-7.750 -0.5830 0.07629 0.07309 -0.0287 1.0000 0.0350
-7.500 -0.5965 0.07309 0.06986 -0.0265 1.0000 0.0355
-7.250 -0.6065 0.07000 0.06671 -0.0243 1.0000 0.0360
-7.000 -0.6149 0.06671 0.06334 -0.0219 1.0000 0.0369
-6.750 -0.6203 0.06350 0.06002 -0.0196 1.0000 0.0378
-6.500 -0.6236 0.06014 0.05648 -0.0170 1.0000 0.0397
-6.250 -0.6234 0.05954 0.05531 -0.0129 1.0000 0.0424
-6.000 -0.6313 0.05396 0.04948 -0.0099 1.0000 0.0432
-5.750 -0.6266 0.04945 0.04506 -0.0083 1.0000 0.0447
-5.500 -0.6188 0.04696 0.04255 -0.0063 1.0000 0.0463
-5.250 -0.6104 0.04458 0.04002 -0.0040 1.0000 0.0486
-5.000 -0.5982 0.04596 0.04065 0.0003 1.0000 0.0555
-4.750 -0.5926 0.03921 0.03398 0.0014 1.0000 0.0580
-4.500 -0.5787 0.03705 0.03175 0.0031 1.0000 0.0610
-4.250 -0.5665 0.03511 0.02939 0.0056 1.0000 0.0707
-4.000 -0.5364 0.02830 0.02164 0.0103 1.0000 0.0273
-3.750 -0.5125 0.02613 0.01880 0.0131 0.9999 0.0206
-3.500 -0.4796 0.02319 0.01555 0.0124 0.9970 0.0189
-3.250 -0.4442 0.02134 0.01335 0.0115 0.9942 0.0183
-3.000 -0.4114 0.01996 0.01182 0.0109 0.9902 0.0183
-2.750 -0.3786 0.01896 0.01071 0.0101 0.9860 0.0188
-2.500 -0.3429 0.01829 0.00994 0.0085 0.9825 0.0207
-2.250 -0.3163 0.01718 0.00884 0.0089 0.9766 0.0436
-2.000 -0.2966 0.01405 0.00972 0.0119 0.9766 0.9114
-1.750 -0.1563 0.01601 0.01117 -0.0089 0.9910 0.9846
-1.500 -0.0741 0.01641 0.01130 -0.0204 0.9950 1.0000
-1.250 -0.0335 0.01643 0.01118 -0.0237 0.9893 1.0000
-1.000 0.0097 0.01654 0.01114 -0.0276 0.9840 1.0000
-0.750 0.0480 0.01657 0.01108 -0.0304 0.9777 1.0000
-0.500 0.0905 0.01662 0.01105 -0.0339 0.9719 1.0000
-0.250 0.1286 0.01661 0.01097 -0.0365 0.9652 1.0000
0.000 0.1711 0.01658 0.01089 -0.0400 0.9591 1.0000
0.250 0.2101 0.01652 0.01080 -0.0426 0.9522 1.0000
0.500 0.2528 0.01641 0.01068 -0.0460 0.9459 1.0000
0.750 0.2925 0.01625 0.01053 -0.0486 0.9388 1.0000
1.000 0.3369 0.01602 0.01031 -0.0521 0.9325 1.0000
1.250 0.3763 0.01577 0.01010 -0.0546 0.9251 1.0000
1.500 0.4231 0.01542 0.00979 -0.0584 0.9192 1.0000
1.750 0.4798 0.01492 0.00937 -0.0642 0.9157 1.0000
2.000 0.5163 0.01447 0.00899 -0.0657 0.9057 1.0000
2.250 0.5530 0.01394 0.00859 -0.0671 0.8958 1.0000
2.500 0.5928 0.01329 0.00802 -0.0690 0.8864 1.0000
2.750 0.6205 0.01273 0.00756 -0.0685 0.8722 1.0000
3.000 0.6437 0.01221 0.00715 -0.0669 0.8539 1.0000
3.250 0.6672 0.01174 0.00676 -0.0654 0.8305 1.0000
3.500 0.7008 0.01116 0.00621 -0.0657 0.7988 1.0000
3.750 0.7403 0.01068 0.00561 -0.0672 0.7436 1.0000
4.000 0.7654 0.01080 0.00543 -0.0661 0.6704 1.0000
4.250 0.7810 0.01124 0.00559 -0.0633 0.5987 1.0000
4.500 0.7929 0.01178 0.00582 -0.0601 0.5290 1.0000
4.750 0.8035 0.01237 0.00612 -0.0567 0.4636 1.0000
5.000 0.8133 0.01300 0.00647 -0.0533 0.4002 1.0000
5.250 0.8235 0.01363 0.00685 -0.0500 0.3401 1.0000
5.500 0.8333 0.01431 0.00726 -0.0468 0.2818 1.0000
5.750 0.8434 0.01500 0.00771 -0.0437 0.2275 1.0000
6.000 0.8535 0.01574 0.00820 -0.0406 0.1766 1.0000
6.250 0.8633 0.01652 0.00877 -0.0374 0.1344 1.0000
6.500 0.8717 0.01742 0.00947 -0.0340 0.0971 1.0000
6.750 0.8794 0.01837 0.01028 -0.0304 0.0715 1.0000
7.000 0.8865 0.01932 0.01120 -0.0265 0.0576 1.0000
7.250 0.8922 0.02042 0.01239 -0.0224 0.0504 1.0000
7.500 0.9011 0.02133 0.01335 -0.0189 0.0447 1.0000
7.750 0.9098 0.02284 0.01489 -0.0155 0.0402 1.0000
8.000 0.9219 0.02361 0.01580 -0.0126 0.0355 1.0000
8.250 0.9369 0.02606 0.01825 -0.0108 0.0300 1.0000
8.500 0.9474 0.02662 0.01904 -0.0074 0.0269 1.0000
8.750 0.9538 0.02737 0.01986 -0.0037 0.0225 1.0000
9.000 0.9654 0.03030 0.02305 -0.0014 0.0190 1.0000
9.250 0.9738 0.03193 0.02498 0.0022 0.0167 1.0000
9.500 0.9813 0.03435 0.02772 0.0055 0.0161 1.0000
9.750 0.9835 0.03695 0.03065 0.0095 0.0158 1.0000
10.000 0.9796 0.03954 0.03356 0.0143 0.0156 1.0000
10.250 0.9699 0.04208 0.03640 0.0197 0.0153 1.0000
10.500 0.9578 0.04490 0.03954 0.0248 0.0157 1.0000
10.750 0.9419 0.04799 0.04294 0.0297 0.0158 1.0000
11.000 0.9247 0.05125 0.04646 0.0337 0.0161 1.0000
11.250 0.9061 0.05465 0.05010 0.0370 0.0163 1.0000
11.500 0.8859 0.05843 0.05411 0.0392 0.0166 1.0000
11.750 0.8658 0.06246 0.05833 0.0402 0.0168 1.0000
12.000 0.8431 0.06731 0.06336 0.0398 0.0169 1.0000
12.250 0.8197 0.07311 0.06932 0.0375 0.0170 1.0000
12.500 0.8001 0.07932 0.07567 0.0339 0.0172 1.0000
12.750 0.7780 0.08741 0.08387 0.0284 0.0175 1.0000
13.000 0.7578 0.09670 0.09324 0.0220 0.0178 1.0000
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Polar data table (+)
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