MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 25 9.98% (mh25-il) Reynolds number: 200,000 Max Cl/Cd: 58.81 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh25-il-200000-n5.txt Download as CSV file: xf-mh25-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4969 0.08976 0.08633 -0.0340 1.0000 0.0106
-9.000 -0.5078 0.08594 0.08256 -0.0345 1.0000 0.0105
-8.750 -0.5206 0.08208 0.07875 -0.0354 1.0000 0.0103
-8.500 -0.5401 0.07785 0.07455 -0.0366 1.0000 0.0102
-8.250 -0.5578 0.07457 0.07125 -0.0359 0.9994 0.0102
-8.000 -0.5650 0.06986 0.06646 -0.0376 0.9956 0.0100
-7.750 -0.5659 0.06480 0.06127 -0.0393 0.9920 0.0097
-7.500 -0.5667 0.05982 0.05613 -0.0398 0.9879 0.0093
-7.250 -0.5623 0.05515 0.05125 -0.0401 0.9846 0.0090
-7.000 -0.5559 0.05001 0.04583 -0.0400 0.9817 0.0085
-6.750 -0.5532 0.04598 0.04153 -0.0376 0.9773 0.0081
-6.500 -0.5455 0.04112 0.03626 -0.0355 0.9736 0.0076
-6.250 -0.5334 0.03589 0.03048 -0.0335 0.9709 0.0071
-6.000 -0.5198 0.03208 0.02613 -0.0310 0.9679 0.0067
-5.750 -0.5065 0.02932 0.02291 -0.0281 0.9641 0.0064
-5.500 -0.4859 0.02708 0.02026 -0.0268 0.9614 0.0063
-5.250 -0.4614 0.02517 0.01797 -0.0261 0.9594 0.0063
-5.000 -0.4340 0.02360 0.01609 -0.0261 0.9578 0.0062
-4.750 -0.4056 0.02183 0.01403 -0.0261 0.9566 0.0063
-4.500 -0.3879 0.02060 0.01263 -0.0240 0.9526 0.0064
-4.250 -0.3651 0.01943 0.01133 -0.0230 0.9495 0.0066
-4.000 -0.3391 0.01848 0.01021 -0.0227 0.9471 0.0069
-3.750 -0.3106 0.01768 0.00929 -0.0229 0.9450 0.0077
-3.500 -0.2798 0.01707 0.00854 -0.0236 0.9434 0.0084
-3.250 -0.2630 0.01663 0.00800 -0.0212 0.9380 0.0109
-3.000 -0.2374 0.01603 0.00740 -0.0208 0.9346 0.0224
-2.750 -0.2145 0.01471 0.00693 -0.0205 0.9319 0.1777
-2.500 -0.1905 0.01358 0.00663 -0.0205 0.9298 0.3798
-2.250 -0.1883 0.01258 0.00643 -0.0153 0.9219 0.5749
-2.000 -0.1364 0.01248 0.00733 -0.0187 0.9239 0.8591
-1.750 -0.1017 0.01273 0.00746 -0.0196 0.9212 0.8938
-1.500 -0.0667 0.01291 0.00752 -0.0206 0.9188 0.9149
-1.250 -0.0168 0.01326 0.00773 -0.0248 0.9182 0.9306
-1.000 0.0409 0.01358 0.00794 -0.0307 0.9183 0.9435
-0.750 0.0953 0.01363 0.00789 -0.0363 0.9177 0.9480
-0.500 0.1253 0.01364 0.00784 -0.0367 0.9124 0.9560
-0.250 0.1737 0.01356 0.00771 -0.0411 0.9096 0.9591
0.000 0.2202 0.01341 0.00752 -0.0451 0.9067 0.9624
0.250 0.2640 0.01320 0.00729 -0.0484 0.9039 0.9654
0.500 0.2916 0.01309 0.00718 -0.0484 0.8957 0.9705
0.750 0.3333 0.01280 0.00689 -0.0513 0.8911 0.9720
1.000 0.3651 0.01260 0.00671 -0.0522 0.8819 0.9752
1.250 0.3983 0.01235 0.00650 -0.0533 0.8735 0.9779
1.500 0.4279 0.01214 0.00630 -0.0536 0.8632 0.9810
1.750 0.4563 0.01194 0.00614 -0.0537 0.8479 0.9837
2.000 0.4881 0.01168 0.00592 -0.0545 0.8303 0.9857
2.250 0.5246 0.01133 0.00563 -0.0561 0.8093 0.9868
2.500 0.5640 0.01096 0.00521 -0.0582 0.7765 0.9871
2.750 0.6013 0.01074 0.00483 -0.0598 0.7290 0.9873
3.000 0.6308 0.01084 0.00468 -0.0599 0.6688 0.9888
3.250 0.6551 0.01114 0.00473 -0.0592 0.6081 0.9910
3.500 0.6768 0.01153 0.00487 -0.0581 0.5482 0.9935
3.750 0.6998 0.01192 0.00503 -0.0574 0.4891 0.9956
4.000 0.7223 0.01238 0.00524 -0.0568 0.4291 0.9980
4.250 0.7447 0.01287 0.00550 -0.0561 0.3727 1.0000
4.500 0.7594 0.01332 0.00584 -0.0538 0.3278 1.0000
4.750 0.7738 0.01380 0.00616 -0.0514 0.2837 1.0000
5.000 0.7882 0.01429 0.00650 -0.0491 0.2425 1.0000
5.250 0.8026 0.01479 0.00687 -0.0468 0.2042 1.0000
5.500 0.8165 0.01533 0.00726 -0.0444 0.1671 1.0000
5.750 0.8303 0.01587 0.00767 -0.0420 0.1341 1.0000
6.250 0.8573 0.01697 0.00859 -0.0370 0.0833 1.0000
6.500 0.8699 0.01756 0.00912 -0.0344 0.0641 1.0000
6.750 0.8823 0.01815 0.00967 -0.0317 0.0491 1.0000
7.000 0.8938 0.01877 0.01036 -0.0288 0.0392 1.0000
7.250 0.9050 0.01937 0.01103 -0.0258 0.0332 1.0000
7.500 0.9136 0.02012 0.01185 -0.0223 0.0289 1.0000
7.750 0.9228 0.02077 0.01264 -0.0189 0.0262 1.0000
8.000 0.9319 0.02141 0.01335 -0.0156 0.0227 1.0000
8.250 0.9342 0.02247 0.01446 -0.0111 0.0198 1.0000
8.500 0.9409 0.02314 0.01527 -0.0073 0.0184 1.0000
8.750 0.9488 0.02369 0.01593 -0.0038 0.0157 1.0000
9.000 0.9547 0.02441 0.01673 -0.0002 0.0134 1.0000
9.250 0.9597 0.02536 0.01778 0.0035 0.0107 1.0000
9.500 0.9668 0.02628 0.01883 0.0068 0.0093 1.0000
9.750 0.9743 0.02722 0.01989 0.0099 0.0081 1.0000
10.000 0.9796 0.02843 0.02121 0.0130 0.0072 1.0000
10.250 0.9785 0.03055 0.02351 0.0170 0.0063 1.0000
10.500 0.9834 0.03221 0.02544 0.0199 0.0061 1.0000
10.750 0.9865 0.03417 0.02766 0.0229 0.0058 1.0000
11.000 0.9877 0.03630 0.03005 0.0259 0.0055 1.0000
11.250 0.9862 0.03864 0.03267 0.0289 0.0053 1.0000
11.500 0.9816 0.04122 0.03552 0.0318 0.0052 1.0000
11.750 0.9745 0.04399 0.03856 0.0344 0.0051 1.0000
12.000 0.9632 0.04721 0.04206 0.0367 0.0050 1.0000
12.250 0.9489 0.05088 0.04600 0.0384 0.0049 1.0000
12.500 0.9351 0.05470 0.05005 0.0391 0.0049 1.0000
12.750 0.9179 0.05933 0.05492 0.0388 0.0049 1.0000
13.000 0.9014 0.06438 0.06017 0.0373 0.0050 1.0000
13.250 0.8818 0.07068 0.06667 0.0343 0.0049 1.0000
13.500 0.8639 0.07755 0.07371 0.0303 0.0051 1.0000
13.750 0.8432 0.08605 0.08237 0.0249 0.0052 1.0000
14.000 0.8237 0.09524 0.09168 0.0191 0.0053 1.0000
14.250 0.8016 0.10588 0.10241 0.0129 0.0054 1.0000
14.500 0.7779 0.11723 0.11375 0.0071 0.0057 1.0000
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Polar data table (+)
Polar graphs
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