MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 24 9.01% (mh24-il) Reynolds number: 500,000 Max Cl/Cd: 79.5 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh24-il-500000.txt Download as CSV file: xf-mh24-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4776 0.08597 0.08382 -0.0351 1.0000 0.0151
-8.750 -0.4894 0.08263 0.08051 -0.0352 1.0000 0.0151
-8.500 -0.5054 0.07905 0.07697 -0.0362 1.0000 0.0151
-8.250 -0.5259 0.07610 0.07402 -0.0350 1.0000 0.0150
-8.000 -0.5484 0.07421 0.07212 -0.0312 1.0000 0.0150
-7.750 -0.5639 0.07139 0.06926 -0.0285 1.0000 0.0150
-7.500 -0.5718 0.06786 0.06566 -0.0271 0.9996 0.0151
-7.250 -0.5622 0.06274 0.06039 -0.0296 0.9970 0.0151
-7.000 -0.5509 0.05773 0.05519 -0.0315 0.9945 0.0151
-6.750 -0.5413 0.05349 0.05075 -0.0319 0.9916 0.0152
-6.500 -0.5304 0.04940 0.04642 -0.0318 0.9882 0.0152
-6.250 -0.5335 0.04018 0.03676 -0.0316 0.9843 0.0160
-6.000 -0.5157 0.03642 0.03280 -0.0323 0.9825 0.0169
-5.750 -0.4992 0.03411 0.03035 -0.0315 0.9795 0.0177
-5.500 -0.4823 0.03188 0.02792 -0.0304 0.9757 0.0188
-5.250 -0.4593 0.02952 0.02530 -0.0301 0.9731 0.0203
-5.000 -0.4313 0.02732 0.02275 -0.0301 0.9712 0.0228
-4.750 -0.3942 0.02821 0.02333 -0.0309 0.9698 0.0252
-4.000 -0.3275 0.01708 0.01113 -0.0260 0.9611 0.0125
-3.750 -0.2965 0.01507 0.00889 -0.0260 0.9596 0.0104
-3.500 -0.2644 0.01375 0.00742 -0.0265 0.9581 0.0094
-3.250 -0.2303 0.01295 0.00652 -0.0277 0.9567 0.0089
-3.000 -0.2059 0.01236 0.00584 -0.0268 0.9528 0.0090
-2.750 -0.1788 0.01193 0.00529 -0.0265 0.9488 0.0090
-2.500 -0.1439 0.01149 0.00471 -0.0278 0.9467 0.0114
-2.250 -0.1128 0.01026 0.00426 -0.0290 0.9448 0.2028
-2.000 -0.0926 0.00841 0.00401 -0.0284 0.9426 0.6108
-1.750 -0.0869 0.00769 0.00416 -0.0230 0.9350 0.8271
-1.500 -0.0540 0.00804 0.00467 -0.0226 0.9333 0.9212
-1.250 -0.0154 0.00813 0.00467 -0.0244 0.9317 0.9320
-1.000 0.0241 0.00822 0.00469 -0.0264 0.9303 0.9410
-0.750 0.0739 0.00830 0.00472 -0.0307 0.9296 0.9450
-0.500 0.1369 0.00844 0.00480 -0.0379 0.9298 0.9498
-0.250 0.1711 0.00849 0.00483 -0.0389 0.9248 0.9567
0.000 0.2182 0.00842 0.00473 -0.0429 0.9217 0.9588
0.250 0.2605 0.00828 0.00458 -0.0458 0.9181 0.9612
0.500 0.2953 0.00818 0.00448 -0.0471 0.9127 0.9654
0.750 0.3261 0.00806 0.00435 -0.0476 0.9053 0.9701
1.000 0.3669 0.00789 0.00418 -0.0502 0.8985 0.9726
1.250 0.4032 0.00770 0.00400 -0.0519 0.8900 0.9757
1.500 0.4323 0.00759 0.00390 -0.0521 0.8775 0.9800
1.750 0.4637 0.00741 0.00373 -0.0528 0.8622 0.9830
2.000 0.4980 0.00719 0.00350 -0.0541 0.8377 0.9851
2.250 0.5304 0.00705 0.00325 -0.0549 0.7986 0.9874
2.500 0.5592 0.00712 0.00312 -0.0550 0.7425 0.9900
2.750 0.5841 0.00740 0.00310 -0.0544 0.6749 0.9928
3.000 0.6102 0.00771 0.00312 -0.0543 0.6047 0.9950
3.250 0.6376 0.00802 0.00317 -0.0545 0.5365 0.9971
3.500 0.6644 0.00840 0.00329 -0.0548 0.4654 0.9991
3.750 0.6871 0.00881 0.00344 -0.0541 0.4012 1.0000
4.000 0.7055 0.00923 0.00363 -0.0525 0.3457 1.0000
4.250 0.7241 0.00963 0.00384 -0.0510 0.2958 1.0000
4.500 0.7418 0.01012 0.00408 -0.0494 0.2374 1.0000
4.750 0.7596 0.01062 0.00434 -0.0477 0.1857 1.0000
5.000 0.7778 0.01106 0.00462 -0.0461 0.1466 1.0000
5.250 0.7962 0.01148 0.00497 -0.0446 0.1149 1.0000
5.500 0.8138 0.01195 0.00531 -0.0428 0.0849 1.0000
5.750 0.8308 0.01247 0.00570 -0.0410 0.0584 1.0000
6.000 0.8476 0.01298 0.00611 -0.0391 0.0386 1.0000
6.250 0.8636 0.01355 0.00668 -0.0369 0.0274 1.0000
6.500 0.8804 0.01399 0.00713 -0.0350 0.0214 1.0000
6.750 0.8975 0.01437 0.00754 -0.0330 0.0176 1.0000
7.000 0.9104 0.01510 0.00835 -0.0303 0.0134 1.0000
7.250 0.9197 0.01616 0.00950 -0.0267 0.0065 1.0000
7.500 0.9303 0.01700 0.01047 -0.0234 0.0059 1.0000
7.750 0.9391 0.01793 0.01154 -0.0198 0.0054 1.0000
8.000 0.9471 0.01895 0.01270 -0.0161 0.0050 1.0000
8.250 0.9540 0.02014 0.01404 -0.0122 0.0049 1.0000
8.500 0.9615 0.02141 0.01553 -0.0085 0.0048 1.0000
8.750 0.9685 0.02306 0.01740 -0.0048 0.0048 1.0000
9.000 0.9754 0.02501 0.01959 -0.0012 0.0048 1.0000
9.250 0.9796 0.02759 0.02250 0.0028 0.0049 1.0000
9.500 0.9797 0.03064 0.02592 0.0071 0.0051 1.0000
9.750 0.9738 0.03407 0.02974 0.0120 0.0053 1.0000
10.000 0.9647 0.03691 0.03288 0.0171 0.0055 1.0000
10.250 0.9493 0.03987 0.03611 0.0225 0.0057 1.0000
10.500 0.9290 0.04337 0.03989 0.0275 0.0059 1.0000
10.750 0.9142 0.04628 0.04300 0.0308 0.0060 1.0000
11.000 0.8913 0.05026 0.04720 0.0335 0.0061 1.0000
11.250 0.8743 0.05388 0.05099 0.0346 0.0062 1.0000
11.500 0.8515 0.05886 0.05614 0.0341 0.0063 1.0000
11.750 0.8362 0.06365 0.06108 0.0320 0.0063 1.0000
12.000 0.8153 0.07062 0.06820 0.0275 0.0063 1.0000
12.250 0.7967 0.07911 0.07681 0.0211 0.0063 1.0000
12.500 0.7814 0.08856 0.08636 0.0143 0.0062 1.0000
12.750 0.7571 0.10202 0.09987 0.0070 0.0063 1.0000
13.000 0.7341 0.11375 0.11152 0.0021 0.0065 1.0000
13.250 0.7203 0.12235 0.12008 -0.0017 0.0067 1.0000
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Polar data table (+)
Polar graphs
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