MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 24 9.01% (mh24-il) Reynolds number: 500,000 Max Cl/Cd: 61.51 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh24-il-500000-n5.txt Download as CSV file: xf-mh24-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4798 0.09542 0.09315 -0.0327 1.0000 0.0084
-9.750 -0.4821 0.09187 0.08963 -0.0336 1.0000 0.0086
-9.250 -0.4954 0.08436 0.08220 -0.0349 1.0000 0.0086
-6.750 -0.4444 0.03509 0.03158 -0.0591 0.9703 0.0067
-6.500 -0.4386 0.03053 0.02662 -0.0567 0.9665 0.0061
-6.250 -0.4281 0.02714 0.02287 -0.0541 0.9625 0.0057
-6.000 -0.4128 0.02359 0.01887 -0.0519 0.9596 0.0052
-5.750 -0.3933 0.01988 0.01461 -0.0499 0.9575 0.0045
-5.500 -0.3688 0.01764 0.01199 -0.0490 0.9560 0.0042
-5.250 -0.3474 0.01644 0.01057 -0.0476 0.9533 0.0041
-5.000 -0.3251 0.01534 0.00927 -0.0463 0.9505 0.0040
-4.750 -0.3010 0.01446 0.00826 -0.0455 0.9481 0.0039
-4.500 -0.2762 0.01364 0.00733 -0.0449 0.9460 0.0039
-4.250 -0.2513 0.01279 0.00638 -0.0443 0.9440 0.0039
-4.000 -0.2271 0.01209 0.00560 -0.0435 0.9417 0.0039
-3.750 -0.2068 0.01155 0.00497 -0.0419 0.9374 0.0039
-3.500 -0.1834 0.01103 0.00436 -0.0409 0.9341 0.0040
-3.250 -0.1577 0.01064 0.00387 -0.0404 0.9315 0.0042
-3.000 -0.1309 0.01030 0.00341 -0.0400 0.9292 0.0047
-2.750 -0.1080 0.01011 0.00315 -0.0389 0.9247 0.0052
-2.500 -0.0844 0.00970 0.00285 -0.0380 0.9207 0.0338
-2.250 -0.0620 0.00902 0.00260 -0.0371 0.9172 0.1421
-2.000 -0.0483 0.00790 0.00241 -0.0348 0.9119 0.3853
-1.750 -0.0366 0.00690 0.00223 -0.0317 0.9063 0.6046
-1.500 -0.0176 0.00633 0.00207 -0.0297 0.9026 0.7263
-1.250 0.0029 0.00609 0.00221 -0.0276 0.8965 0.8312
-1.000 0.0301 0.00607 0.00223 -0.0271 0.8917 0.8690
-0.750 0.0556 0.00606 0.00220 -0.0264 0.8861 0.8877
-0.500 0.0818 0.00610 0.00223 -0.0257 0.8792 0.9041
-0.250 0.1081 0.00615 0.00226 -0.0250 0.8720 0.9180
0.000 0.1337 0.00617 0.00225 -0.0243 0.8634 0.9274
0.250 0.1623 0.00620 0.00226 -0.0243 0.8526 0.9324
0.500 0.1902 0.00621 0.00224 -0.0241 0.8394 0.9377
0.750 0.2172 0.00621 0.00219 -0.0237 0.8222 0.9434
1.000 0.2511 0.00628 0.00216 -0.0247 0.7970 0.9470
1.250 0.2810 0.00640 0.00214 -0.0250 0.7636 0.9513
1.500 0.3041 0.00658 0.00214 -0.0238 0.7252 0.9563
1.750 0.3340 0.00680 0.00219 -0.0243 0.6819 0.9579
2.000 0.3617 0.00706 0.00226 -0.0244 0.6360 0.9598
2.250 0.3882 0.00734 0.00234 -0.0243 0.5889 0.9618
2.500 0.4127 0.00762 0.00243 -0.0237 0.5410 0.9645
2.750 0.4293 0.00787 0.00252 -0.0215 0.5008 0.9690
3.000 0.4582 0.00817 0.00267 -0.0220 0.4527 0.9700
3.250 0.4865 0.00851 0.00281 -0.0225 0.4042 0.9711
3.500 0.5143 0.00882 0.00297 -0.0229 0.3588 0.9724
3.750 0.5413 0.00914 0.00313 -0.0231 0.3166 0.9738
4.000 0.5674 0.00951 0.00332 -0.0232 0.2713 0.9755
4.250 0.5928 0.00983 0.00353 -0.0230 0.2353 0.9774
4.500 0.6162 0.01018 0.00375 -0.0224 0.1991 0.9798
4.750 0.6393 0.01052 0.00398 -0.0218 0.1673 0.9821
5.000 0.6669 0.01094 0.00425 -0.0222 0.1300 0.9830
5.250 0.6937 0.01142 0.00455 -0.0226 0.0934 0.9841
5.500 0.7206 0.01184 0.00487 -0.0228 0.0691 0.9854
5.750 0.7476 0.01220 0.00525 -0.0231 0.0531 0.9867
6.000 0.7744 0.01259 0.00561 -0.0233 0.0403 0.9883
6.250 0.8003 0.01302 0.00602 -0.0233 0.0289 0.9901
6.500 0.8249 0.01350 0.00645 -0.0231 0.0182 0.9919
6.750 0.8492 0.01396 0.00691 -0.0228 0.0132 0.9936
7.000 0.8759 0.01436 0.00736 -0.0231 0.0103 0.9948
7.250 0.9021 0.01487 0.00788 -0.0232 0.0061 0.9963
7.500 0.9273 0.01549 0.00853 -0.0232 0.0034 0.9979
7.750 0.9528 0.01617 0.00931 -0.0232 0.0026 0.9995
8.000 0.9697 0.01681 0.01011 -0.0214 0.0021 1.0000
8.250 0.9817 0.01740 0.01081 -0.0185 0.0020 1.0000
8.500 0.9929 0.01802 0.01154 -0.0155 0.0019 1.0000
8.750 1.0024 0.01877 0.01241 -0.0123 0.0018 1.0000
9.000 1.0117 0.01955 0.01332 -0.0090 0.0017 1.0000
9.250 1.0192 0.02054 0.01446 -0.0055 0.0016 1.0000
9.500 1.0262 0.02162 0.01569 -0.0020 0.0016 1.0000
9.750 1.0321 0.02288 0.01714 0.0016 0.0016 1.0000
10.000 1.0386 0.02395 0.01835 0.0049 0.0016 1.0000
10.250 1.0418 0.02532 0.01992 0.0087 0.0015 1.0000
10.500 1.0401 0.02731 0.02216 0.0130 0.0015 1.0000
10.750 1.0447 0.02866 0.02368 0.0160 0.0015 1.0000
11.000 1.0396 0.03100 0.02631 0.0200 0.0015 1.0000
11.250 1.0408 0.03266 0.02815 0.0228 0.0015 1.0000
11.500 1.0321 0.03530 0.03106 0.0263 0.0015 1.0000
11.750 1.0293 0.03734 0.03329 0.0288 0.0015 1.0000
12.000 1.0166 0.04047 0.03666 0.0313 0.0015 1.0000
12.250 1.0023 0.04397 0.04040 0.0330 0.0015 1.0000
12.500 0.9929 0.04722 0.04386 0.0336 0.0015 1.0000
12.750 0.9740 0.05215 0.04901 0.0329 0.0015 1.0000
13.000 0.9556 0.05787 0.05489 0.0306 0.0015 1.0000
13.250 0.9424 0.06372 0.06089 0.0272 0.0015 1.0000
13.500 0.9293 0.07044 0.06776 0.0227 0.0015 1.0000
13.750 0.9121 0.07901 0.07647 0.0171 0.0015 1.0000
14.000 0.9005 0.08668 0.08425 0.0124 0.0016 1.0000
14.250 0.8760 0.09773 0.09540 0.0062 0.0016 1.0000
14.500 0.8597 0.10659 0.10432 0.0019 0.0016 1.0000
14.750 0.8319 0.11857 0.11636 -0.0037 0.0016 1.0000
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Polar data table (+)
Polar graphs
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