MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 24 9.01% (mh24-il) Reynolds number: 200,000 Max Cl/Cd: 68.43 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh24-il-200000.txt Download as CSV file: xf-mh24-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 24 9.01%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4928 0.08873 0.08536 -0.0425 1.0000 0.0364
-8.750 -0.5076 0.08543 0.08207 -0.0429 1.0000 0.0364
-8.500 -0.5266 0.08325 0.07989 -0.0404 1.0000 0.0364
-8.250 -0.5462 0.08116 0.07780 -0.0370 1.0000 0.0364
-8.000 -0.5600 0.07871 0.07530 -0.0344 1.0000 0.0365
-7.750 -0.5723 0.07614 0.07264 -0.0318 1.0000 0.0365
-7.500 -0.5823 0.07350 0.06989 -0.0290 1.0000 0.0366
-7.250 -0.5997 0.06702 0.06339 -0.0269 1.0000 0.0373
-7.000 -0.6003 0.06310 0.05954 -0.0249 1.0000 0.0383
-6.750 -0.6001 0.06041 0.05685 -0.0226 1.0000 0.0391
-6.500 -0.5995 0.05775 0.05413 -0.0202 1.0000 0.0403
-6.250 -0.5977 0.05505 0.05133 -0.0179 1.0000 0.0416
-6.000 -0.5947 0.05217 0.04830 -0.0156 1.0000 0.0435
-5.750 -0.5894 0.04926 0.04512 -0.0131 1.0000 0.0469
-5.500 -0.5894 0.04598 0.04124 -0.0095 1.0000 0.0506
-5.250 -0.5792 0.04265 0.03800 -0.0081 1.0000 0.0523
-5.000 -0.5681 0.04036 0.03564 -0.0062 1.0000 0.0551
-4.750 -0.5587 0.03858 0.03322 -0.0030 1.0000 0.0636
-4.500 -0.5445 0.03547 0.03015 -0.0018 1.0000 0.0661
-4.250 -0.5288 0.03366 0.02814 0.0001 1.0000 0.0716
-4.000 -0.5144 0.03140 0.02568 0.0019 1.0000 0.0802
-3.750 -0.4765 0.02471 0.01762 0.0069 1.0000 0.0241
-3.500 -0.4549 0.02212 0.01468 0.0086 1.0000 0.0221
-3.250 -0.4321 0.02030 0.01257 0.0102 1.0000 0.0204
-3.000 -0.4094 0.01882 0.01088 0.0117 1.0000 0.0197
-2.750 -0.3865 0.01770 0.00964 0.0129 0.9997 0.0190
-2.500 -0.3516 0.01669 0.00856 0.0117 0.9960 0.0199
-2.250 -0.3169 0.01604 0.00779 0.0103 0.9919 0.0217
-2.000 -0.2830 0.01533 0.00690 0.0093 0.9869 0.0346
-1.750 -0.1522 0.01352 0.00875 -0.0081 1.0000 0.9932
-1.500 -0.1002 0.01369 0.00869 -0.0136 1.0000 1.0000
-1.250 -0.0842 0.01371 0.00861 -0.0121 0.9992 1.0000
-1.000 -0.0377 0.01388 0.00860 -0.0165 0.9941 1.0000
-0.750 0.0044 0.01392 0.00854 -0.0200 0.9878 1.0000
-0.500 0.0509 0.01408 0.00860 -0.0244 0.9827 1.0000
-0.250 0.0918 0.01409 0.00853 -0.0276 0.9756 1.0000
0.000 0.1394 0.01416 0.00854 -0.0320 0.9703 1.0000
0.250 0.1794 0.01411 0.00846 -0.0348 0.9625 1.0000
0.500 0.2293 0.01405 0.00841 -0.0396 0.9572 1.0000
0.750 0.2689 0.01393 0.00829 -0.0422 0.9488 1.0000
1.000 0.3213 0.01374 0.00812 -0.0473 0.9440 1.0000
1.250 0.3623 0.01351 0.00793 -0.0500 0.9353 1.0000
1.500 0.4201 0.01313 0.00763 -0.0560 0.9309 1.0000
1.750 0.4617 0.01274 0.00732 -0.0586 0.9212 1.0000
2.000 0.5048 0.01226 0.00692 -0.0613 0.9122 1.0000
2.250 0.5407 0.01176 0.00650 -0.0624 0.9005 1.0000
2.500 0.5645 0.01135 0.00621 -0.0609 0.8832 1.0000
2.750 0.5888 0.01090 0.00584 -0.0595 0.8640 1.0000
3.000 0.6099 0.01054 0.00554 -0.0575 0.8375 1.0000
3.250 0.6348 0.01016 0.00519 -0.0562 0.8018 1.0000
3.500 0.6642 0.00987 0.00480 -0.0555 0.7457 1.0000
3.750 0.6864 0.01003 0.00467 -0.0537 0.6752 1.0000
4.000 0.7030 0.01044 0.00477 -0.0512 0.6006 1.0000
4.250 0.7172 0.01097 0.00497 -0.0484 0.5276 1.0000
4.500 0.7306 0.01155 0.00525 -0.0455 0.4560 1.0000
4.750 0.7437 0.01216 0.00558 -0.0428 0.3883 1.0000
5.000 0.7566 0.01281 0.00595 -0.0402 0.3230 1.0000
5.250 0.7700 0.01347 0.00636 -0.0376 0.2618 1.0000
5.500 0.7825 0.01422 0.00688 -0.0351 0.2016 1.0000
5.750 0.7950 0.01502 0.00742 -0.0325 0.1481 1.0000
6.000 0.8071 0.01591 0.00807 -0.0298 0.1031 1.0000
6.250 0.8173 0.01697 0.00893 -0.0267 0.0717 1.0000
6.500 0.8268 0.01809 0.01002 -0.0232 0.0563 1.0000
6.750 0.8377 0.01914 0.01110 -0.0200 0.0474 1.0000
7.000 0.8493 0.02041 0.01247 -0.0169 0.0420 1.0000
7.250 0.8625 0.02131 0.01340 -0.0143 0.0360 1.0000
7.500 0.8767 0.02301 0.01524 -0.0118 0.0311 1.0000
8.000 0.9000 0.02491 0.01737 -0.0063 0.0173 1.0000
8.250 0.9121 0.02685 0.01943 -0.0037 0.0151 1.0000
8.500 0.9230 0.03077 0.02371 -0.0010 0.0141 1.0000
8.750 0.9265 0.03478 0.02819 0.0027 0.0136 1.0000
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Polar data table (+)
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