MH 82 13.31% (mh82-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 82 13.31% (mh82-il) Reynolds number: 100,000 Max Cl/Cd: 29.61 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh82-il-100000.txt Download as CSV file: xf-mh82-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 82 13.31%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3548 0.11508 0.11109 0.0079 1.0000 0.0868
-9.250 -0.3645 0.11280 0.10891 0.0019 1.0000 0.0896
-9.000 -0.3823 0.11052 0.10678 -0.0063 1.0000 0.0904
-8.750 -0.3418 0.10411 0.10040 -0.0004 1.0000 0.0929
-8.500 -0.3262 0.10074 0.09711 -0.0014 1.0000 0.0956
-8.250 -0.3171 0.09730 0.09378 -0.0048 1.0000 0.0995
-8.000 -0.3336 0.09413 0.09078 -0.0191 0.9593 0.1036
-7.750 -0.3051 0.08862 0.08518 -0.0188 0.9083 0.1060
-7.500 -0.2919 0.08620 0.08264 -0.0158 0.8700 0.1089
-7.250 -0.2906 0.08382 0.08018 -0.0156 0.8416 0.1122
-7.000 -0.3073 0.08097 0.07730 -0.0209 0.8205 0.1170
-6.750 -0.3184 0.07636 0.07257 -0.0272 0.8041 0.1200
-6.500 -0.3006 0.07392 0.07013 -0.0225 0.7858 0.1225
-6.250 -0.2912 0.07130 0.06744 -0.0222 0.7693 0.1266
-6.000 -0.2977 0.06676 0.06265 -0.0299 0.7571 0.1358
-5.750 -0.2810 0.06405 0.05997 -0.0272 0.7419 0.1387
-5.500 -0.2688 0.06138 0.05717 -0.0273 0.7290 0.1453
-5.250 -0.2595 0.05773 0.05334 -0.0293 0.7166 0.1545
-5.000 -0.2470 0.05496 0.05030 -0.0312 0.7039 0.1690
-4.750 -0.2228 0.03863 0.03212 -0.0358 0.7017 0.0660
-4.500 -0.2016 0.03570 0.02890 -0.0351 0.6894 0.0643
-4.250 -0.1798 0.03293 0.02560 -0.0339 0.6792 0.0630
-4.000 -0.1547 0.03021 0.02234 -0.0331 0.6663 0.0610
-3.750 -0.1284 0.02790 0.01943 -0.0320 0.6546 0.0594
-3.500 -0.1025 0.02627 0.01741 -0.0307 0.6445 0.0600
-3.250 -0.0748 0.02492 0.01589 -0.0301 0.6315 0.0618
-3.000 -0.0472 0.02394 0.01465 -0.0292 0.6200 0.0663
-2.750 -0.0215 0.02284 0.01351 -0.0283 0.6101 0.0733
-2.500 0.0055 0.02180 0.01250 -0.0276 0.5980 0.0821
-2.250 0.0313 0.02099 0.01168 -0.0265 0.5883 0.1033
-2.000 0.0542 0.01943 0.01072 -0.0254 0.5782 0.1937
-1.750 0.0745 0.01798 0.01035 -0.0241 0.5688 0.4037
-1.500 0.0993 0.01656 0.01057 -0.0202 0.5595 0.8642
-1.250 0.2149 0.01664 0.00998 -0.0343 0.5420 1.0000
-1.000 0.2376 0.01681 0.00993 -0.0337 0.5324 1.0000
-0.750 0.2601 0.01694 0.00977 -0.0327 0.5245 1.0000
-0.500 0.2835 0.01720 0.00985 -0.0321 0.5153 1.0000
-0.250 0.3065 0.01736 0.00975 -0.0311 0.5077 1.0000
0.000 0.3302 0.01767 0.00991 -0.0305 0.4991 1.0000
0.250 0.3538 0.01789 0.00993 -0.0297 0.4916 1.0000
0.500 0.3777 0.01824 0.01012 -0.0290 0.4847 1.0000
0.750 0.4018 0.01856 0.01032 -0.0284 0.4768 1.0000
1.000 0.4258 0.01881 0.01030 -0.0274 0.4714 1.0000
1.250 0.4500 0.01929 0.01080 -0.0271 0.4628 1.0000
1.500 0.4745 0.01957 0.01089 -0.0263 0.4570 1.0000
1.750 0.4987 0.02008 0.01133 -0.0259 0.4509 1.0000
2.000 0.5230 0.02056 0.01175 -0.0254 0.4442 1.0000
2.250 0.5480 0.02085 0.01185 -0.0246 0.4392 1.0000
2.500 0.5719 0.02150 0.01253 -0.0243 0.4327 1.0000
2.750 0.5965 0.02199 0.01296 -0.0239 0.4267 1.0000
3.000 0.6220 0.02235 0.01317 -0.0232 0.4226 1.0000
3.250 0.6457 0.02317 0.01404 -0.0230 0.4169 1.0000
3.500 0.6699 0.02379 0.01467 -0.0227 0.4111 1.0000
3.750 0.6957 0.02413 0.01488 -0.0222 0.4068 1.0000
4.000 0.7196 0.02493 0.01569 -0.0219 0.4021 1.0000
4.250 0.7421 0.02595 0.01682 -0.0218 0.3965 1.0000
4.500 0.7672 0.02646 0.01728 -0.0214 0.3922 1.0000
4.750 0.7939 0.02681 0.01748 -0.0209 0.3888 1.0000
5.000 0.8127 0.02835 0.01926 -0.0210 0.3827 1.0000
5.250 0.8354 0.02927 0.02023 -0.0207 0.3781 1.0000
5.500 0.8611 0.02976 0.02065 -0.0203 0.3747 1.0000
5.750 0.8880 0.03021 0.02097 -0.0199 0.3718 1.0000
6.000 0.8981 0.03281 0.02399 -0.0201 0.3650 1.0000
6.250 0.9204 0.03369 0.02489 -0.0198 0.3609 1.0000
6.500 0.9475 0.03400 0.02513 -0.0194 0.3580 1.0000
6.750 0.9697 0.03510 0.02624 -0.0191 0.3548 1.0000
7.000 0.9607 0.03986 0.03147 -0.0194 0.3475 1.0000
7.250 0.9833 0.04057 0.03219 -0.0189 0.3439 1.0000
7.500 1.0171 0.04007 0.03158 -0.0183 0.3416 1.0000
7.750 0.6764 0.08864 0.08090 -0.0387 0.3429 1.0000
8.000 0.6970 0.09064 0.08290 -0.0384 0.3412 1.0000
8.250 0.7144 0.09326 0.08555 -0.0383 0.3403 1.0000
8.500 0.7299 0.09650 0.08879 -0.0385 0.3397 1.0000
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Polar data table (+)
Polar graphs
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