MH 23 8% (mh23-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 23 8% (mh23-il) Reynolds number: 500,000 Max Cl/Cd: 83.85 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh23-il-500000.txt Download as CSV file: xf-mh23-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 23 8%
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4087 0.09355 0.09141 -0.0257 1.0000 0.0106
-9.750 -0.4090 0.08919 0.08707 -0.0272 1.0000 0.0106
-9.500 -0.4083 0.08552 0.08341 -0.0279 1.0000 0.0111
-9.250 -0.4091 0.08138 0.07928 -0.0292 1.0000 0.0113
-9.000 -0.4106 0.07731 0.07523 -0.0303 1.0000 0.0116
-8.750 -0.4925 0.08004 0.07791 -0.0331 1.0000 0.0102
-8.500 -0.4921 0.07653 0.07443 -0.0356 1.0000 0.0100
-8.250 -0.5083 0.07236 0.07030 -0.0377 1.0000 0.0101
-8.000 -0.5227 0.07107 0.06902 -0.0344 1.0000 0.0099
-7.750 -0.5359 0.06887 0.06680 -0.0315 1.0000 0.0098
-7.500 -0.5582 0.06462 0.06250 -0.0290 1.0000 0.0100
-7.250 -0.5738 0.06064 0.05844 -0.0266 1.0000 0.0103
-7.000 -0.5805 0.05725 0.05497 -0.0242 1.0000 0.0104
-6.750 -0.5825 0.05335 0.05095 -0.0231 0.9994 0.0108
-6.500 -0.5675 0.04985 0.04732 -0.0248 0.9970 0.0116
-6.250 -0.5487 0.04582 0.04306 -0.0264 0.9947 0.0122
-6.000 -0.5305 0.04257 0.03962 -0.0272 0.9923 0.0137
-5.750 -0.5119 0.03889 0.03570 -0.0272 0.9892 0.0153
-5.500 -0.4767 0.03845 0.03492 -0.0270 0.9869 0.0196
-5.250 -0.4526 0.03551 0.03163 -0.0273 0.9844 0.0197
-5.000 -0.4395 0.02768 0.02329 -0.0274 0.9820 0.0216
-4.750 -0.4194 0.02575 0.02125 -0.0266 0.9785 0.0230
-4.500 -0.3950 0.02394 0.01922 -0.0262 0.9752 0.0250
-4.250 -0.3653 0.02246 0.01747 -0.0263 0.9730 0.0282
-4.000 -0.3367 0.02002 0.01462 -0.0266 0.9711 0.0334
-3.750 -0.3014 0.01625 0.01045 -0.0256 0.9702 0.0155
-3.500 -0.2672 0.01412 0.00804 -0.0259 0.9693 0.0117
-3.250 -0.2437 0.01339 0.00718 -0.0247 0.9649 0.0106
-3.000 -0.2133 0.01273 0.00646 -0.0250 0.9618 0.0100
-2.750 -0.1802 0.01197 0.00563 -0.0260 0.9596 0.0097
-2.500 -0.1449 0.01113 0.00466 -0.0274 0.9578 0.0098
-2.250 -0.1058 0.01058 0.00389 -0.0296 0.9566 0.0118
-2.000 -0.0855 0.00951 0.00354 -0.0283 0.9513 0.1964
-1.750 -0.0687 0.00795 0.00336 -0.0267 0.9465 0.5637
-1.500 -0.0191 0.00719 0.00389 -0.0301 0.9483 0.9339
-1.250 0.0253 0.00729 0.00391 -0.0332 0.9468 0.9475
-1.000 0.0683 0.00736 0.00390 -0.0361 0.9450 0.9566
-0.750 0.1192 0.00737 0.00384 -0.0407 0.9438 0.9615
-0.500 0.1620 0.00743 0.00386 -0.0436 0.9409 0.9700
-0.250 0.2096 0.00739 0.00379 -0.0477 0.9372 0.9751
0.000 0.2433 0.00734 0.00372 -0.0487 0.9319 0.9813
0.250 0.2836 0.00715 0.00352 -0.0512 0.9266 0.9841
0.500 0.3209 0.00696 0.00332 -0.0532 0.9193 0.9880
0.750 0.3554 0.00681 0.00317 -0.0545 0.9112 0.9926
1.000 0.3926 0.00657 0.00292 -0.0564 0.9025 0.9964
1.250 0.4281 0.00634 0.00271 -0.0580 0.8902 1.0000
1.500 0.4483 0.00623 0.00259 -0.0563 0.8730 1.0000
1.750 0.4689 0.00611 0.00246 -0.0546 0.8506 1.0000
2.000 0.4898 0.00603 0.00232 -0.0530 0.8170 1.0000
2.250 0.5098 0.00608 0.00215 -0.0511 0.7636 1.0000
2.500 0.5294 0.00632 0.00212 -0.0492 0.7009 1.0000
2.750 0.5487 0.00666 0.00222 -0.0475 0.6331 1.0000
3.000 0.5682 0.00703 0.00233 -0.0459 0.5660 1.0000
3.250 0.5879 0.00743 0.00246 -0.0444 0.4997 1.0000
3.500 0.6080 0.00783 0.00262 -0.0431 0.4376 1.0000
3.750 0.6283 0.00824 0.00280 -0.0418 0.3767 1.0000
4.000 0.6490 0.00864 0.00303 -0.0406 0.3237 1.0000
4.250 0.6691 0.00910 0.00325 -0.0394 0.2649 1.0000
4.500 0.6886 0.00963 0.00351 -0.0381 0.2023 1.0000
4.750 0.7090 0.01008 0.00378 -0.0369 0.1593 1.0000
5.000 0.7288 0.01058 0.00409 -0.0356 0.1177 1.0000
5.250 0.7477 0.01117 0.00445 -0.0341 0.0746 1.0000
5.500 0.7674 0.01168 0.00483 -0.0328 0.0483 1.0000
5.750 0.7874 0.01215 0.00526 -0.0314 0.0329 1.0000
6.000 0.8072 0.01262 0.00571 -0.0300 0.0229 1.0000
6.250 0.8261 0.01320 0.00630 -0.0284 0.0115 1.0000
6.500 0.8425 0.01417 0.00741 -0.0260 0.0059 1.0000
6.750 0.8581 0.01517 0.00855 -0.0236 0.0047 1.0000
7.000 0.8714 0.01640 0.00996 -0.0208 0.0044 1.0000
7.250 0.8839 0.01780 0.01154 -0.0178 0.0043 1.0000
7.500 0.8967 0.01931 0.01323 -0.0151 0.0042 1.0000
7.750 0.9091 0.02113 0.01528 -0.0122 0.0042 1.0000
8.000 0.9224 0.02287 0.01725 -0.0096 0.0043 1.0000
8.250 0.9351 0.02470 0.01931 -0.0069 0.0044 1.0000
8.500 0.9454 0.02695 0.02189 -0.0038 0.0046 1.0000
8.750 0.9401 0.03257 0.02820 0.0019 0.0055 1.0000
9.000 0.9267 0.03797 0.03414 0.0079 0.0064 1.0000
9.250 0.9102 0.04255 0.03909 0.0132 0.0070 1.0000
9.500 0.8932 0.04622 0.04302 0.0180 0.0074 1.0000
9.750 0.8708 0.04930 0.04629 0.0231 0.0077 1.0000
10.000 0.8499 0.05262 0.04978 0.0264 0.0078 1.0000
10.250 0.8269 0.05666 0.05398 0.0280 0.0080 1.0000
10.500 0.8130 0.06034 0.05779 0.0277 0.0079 1.0000
10.750 0.7933 0.06580 0.06338 0.0249 0.0079 1.0000
11.000 0.7754 0.07305 0.07076 0.0193 0.0078 1.0000
11.250 0.7637 0.08219 0.08001 0.0119 0.0075 1.0000
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Polar data table (+)
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