MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 78 14.47% (mh78-il) Reynolds number: 200,000 Max Cl/Cd: 51.27 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh78-il-200000-n5.txt Download as CSV file: xf-mh78-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 78 14.47%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7103 0.07247 0.06888 0.0076 1.0000 0.0156
-10.750 -0.7570 0.06020 0.05631 -0.0030 1.0000 0.0154
-10.500 -0.7876 0.05417 0.05001 -0.0052 1.0000 0.0153
-10.250 -0.8131 0.04963 0.04520 -0.0043 1.0000 0.0152
-10.000 -0.8301 0.04620 0.04152 -0.0017 1.0000 0.0151
-9.750 -0.8408 0.04286 0.03785 0.0010 1.0000 0.0152
-9.500 -0.8421 0.03974 0.03441 0.0032 1.0000 0.0152
-9.250 -0.8376 0.03689 0.03123 0.0052 1.0000 0.0153
-9.000 -0.8253 0.03444 0.02842 0.0064 0.9102 0.0154
-8.750 -0.8165 0.03266 0.02619 0.0093 0.8288 0.0156
-8.500 -0.8043 0.03097 0.02408 0.0118 0.7859 0.0158
-8.250 -0.7887 0.02940 0.02215 0.0138 0.7526 0.0160
-8.000 -0.7708 0.02798 0.02035 0.0155 0.7243 0.0162
-7.750 -0.7507 0.02681 0.01896 0.0169 0.6989 0.0164
-7.500 -0.7295 0.02584 0.01784 0.0180 0.6751 0.0167
-7.250 -0.7075 0.02496 0.01681 0.0191 0.6532 0.0169
-7.000 -0.6847 0.02411 0.01580 0.0201 0.6332 0.0173
-6.750 -0.6614 0.02332 0.01485 0.0210 0.6139 0.0177
-6.500 -0.6375 0.02259 0.01396 0.0219 0.5959 0.0184
-6.250 -0.6132 0.02187 0.01301 0.0228 0.5790 0.0193
-6.000 -0.5893 0.02122 0.01232 0.0236 0.5627 0.0200
-5.750 -0.5649 0.02062 0.01162 0.0244 0.5471 0.0206
-5.500 -0.5403 0.02000 0.01090 0.0252 0.5321 0.0214
-5.250 -0.5157 0.01939 0.01016 0.0260 0.5181 0.0222
-5.000 -0.4912 0.01881 0.00949 0.0269 0.5046 0.0230
-4.750 -0.4662 0.01830 0.00893 0.0276 0.4911 0.0241
-4.500 -0.4408 0.01784 0.00837 0.0283 0.4789 0.0254
-4.250 -0.4155 0.01739 0.00783 0.0290 0.4667 0.0271
-4.000 -0.3895 0.01701 0.00738 0.0296 0.4548 0.0298
-3.750 -0.3637 0.01664 0.00694 0.0302 0.4437 0.0338
-3.500 -0.3376 0.01626 0.00654 0.0308 0.4326 0.0391
-3.250 -0.3118 0.01588 0.00614 0.0315 0.4230 0.0475
-3.000 -0.2860 0.01547 0.00579 0.0321 0.4126 0.0641
-2.750 -0.2610 0.01500 0.00546 0.0327 0.4033 0.0988
-2.500 -0.2362 0.01450 0.00521 0.0333 0.3936 0.1565
-2.250 -0.2116 0.01407 0.00500 0.0339 0.3852 0.2178
-2.000 -0.1871 0.01364 0.00482 0.0346 0.3769 0.2842
-1.750 -0.1636 0.01320 0.00464 0.0355 0.3691 0.3607
-1.000 -0.0990 0.01155 0.00467 0.0408 0.3472 0.7636
-0.500 -0.0350 0.01200 0.00509 0.0412 0.3327 0.8600
-0.250 -0.0054 0.01219 0.00519 0.0415 0.3262 0.8783
0.000 0.0233 0.01236 0.00526 0.0419 0.3195 0.8930
0.250 0.0508 0.01256 0.00532 0.0425 0.3137 0.9061
0.500 0.0857 0.01276 0.00545 0.0417 0.3078 0.9144
0.750 0.1127 0.01294 0.00553 0.0423 0.3024 0.9256
1.000 0.1543 0.01322 0.00567 0.0402 0.2966 0.9328
1.250 0.1897 0.01346 0.00584 0.0392 0.2911 0.9435
1.500 0.2380 0.01368 0.00597 0.0356 0.2849 0.9493
1.750 0.2704 0.01388 0.00606 0.0350 0.2805 0.9575
2.000 0.3123 0.01404 0.00612 0.0324 0.2760 0.9608
2.250 0.3491 0.01416 0.00620 0.0308 0.2710 0.9649
2.500 0.3798 0.01430 0.00627 0.0304 0.2668 0.9700
2.750 0.4150 0.01444 0.00631 0.0289 0.2628 0.9728
3.000 0.4498 0.01458 0.00640 0.0276 0.2593 0.9755
3.250 0.4825 0.01470 0.00651 0.0266 0.2555 0.9786
3.500 0.5129 0.01484 0.00662 0.0261 0.2516 0.9820
3.750 0.5455 0.01499 0.00669 0.0251 0.2481 0.9843
4.000 0.5784 0.01518 0.00679 0.0240 0.2450 0.9865
4.250 0.6106 0.01533 0.00697 0.0231 0.2419 0.9889
4.500 0.6418 0.01549 0.00715 0.0223 0.2386 0.9913
4.750 0.6723 0.01568 0.00732 0.0217 0.2354 0.9936
5.000 0.7041 0.01585 0.00745 0.0207 0.2323 0.9955
5.250 0.7350 0.01611 0.00762 0.0199 0.2295 0.9975
5.500 0.7665 0.01631 0.00788 0.0190 0.2268 0.9995
5.750 0.7920 0.01655 0.00817 0.0193 0.2242 1.0000
6.000 0.8150 0.01680 0.00843 0.0200 0.2216 1.0000
6.250 0.8377 0.01705 0.00868 0.0208 0.2190 1.0000
6.500 0.8600 0.01733 0.00894 0.0216 0.2166 1.0000
6.750 0.8819 0.01768 0.00922 0.0225 0.2144 1.0000
7.000 0.9040 0.01799 0.00962 0.0233 0.2122 1.0000
7.250 0.9257 0.01831 0.01001 0.0242 0.2099 1.0000
7.500 0.9471 0.01865 0.01039 0.0252 0.2077 1.0000
7.750 0.9681 0.01897 0.01074 0.0261 0.2054 1.0000
8.000 0.9887 0.01931 0.01108 0.0271 0.2033 1.0000
8.250 1.0089 0.01968 0.01143 0.0282 0.2012 1.0000
8.500 1.0287 0.02010 0.01187 0.0293 0.1993 1.0000
8.750 1.0481 0.02052 0.01239 0.0305 0.1973 1.0000
9.000 1.0671 0.02096 0.01291 0.0316 0.1953 1.0000
9.250 1.0857 0.02139 0.01340 0.0329 0.1932 1.0000
9.500 1.1041 0.02181 0.01387 0.0341 0.1912 1.0000
9.750 1.1222 0.02223 0.01431 0.0353 0.1893 1.0000
10.000 1.1402 0.02268 0.01474 0.0366 0.1876 1.0000
10.250 1.1578 0.02321 0.01528 0.0378 0.1859 1.0000
10.500 1.1742 0.02380 0.01601 0.0390 0.1841 1.0000
10.750 1.1903 0.02441 0.01672 0.0402 0.1822 1.0000
11.000 1.2062 0.02501 0.01740 0.0414 0.1802 1.0000
11.250 1.2220 0.02560 0.01806 0.0425 0.1783 1.0000
11.500 1.2376 0.02620 0.01870 0.0436 0.1765 1.0000
11.750 1.2532 0.02682 0.01933 0.0446 0.1750 1.0000
12.000 1.2693 0.02748 0.01997 0.0456 0.1735 1.0000
12.250 1.2780 0.02846 0.02111 0.0468 0.1719 1.0000
12.500 1.2810 0.02956 0.02234 0.0485 0.1701 1.0000
12.750 1.2838 0.03085 0.02375 0.0496 0.1683 1.0000
13.000 1.2878 0.03229 0.02529 0.0501 0.1666 1.0000
13.250 1.2924 0.03383 0.02691 0.0503 0.1650 1.0000
13.500 1.2983 0.03539 0.02852 0.0503 0.1635 1.0000
13.750 1.3076 0.03672 0.02984 0.0503 0.1619 1.0000
14.000 1.3097 0.03881 0.03201 0.0498 0.1603 1.0000
14.250 1.2987 0.04237 0.03578 0.0484 0.1585 1.0000
14.500 1.2869 0.04624 0.03982 0.0467 0.1566 1.0000
14.750 1.2753 0.05024 0.04396 0.0448 0.1546 1.0000
15.000 1.2673 0.05392 0.04772 0.0430 0.1527 1.0000
15.250 1.2665 0.05676 0.05060 0.0418 0.1511 1.0000
15.500 1.2822 0.05749 0.05129 0.0420 0.1495 1.0000
16.000 1.0355 0.10069 0.09517 0.0177 0.1376 1.0000
16.250 1.0773 0.09717 0.09164 0.0199 0.1379 1.0000
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Polar data table (+)
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