MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 78 14.47% (mh78-il) Reynolds number: 200,000 Max Cl/Cd: 42.34 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh78-il-200000.txt Download as CSV file: xf-mh78-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5655 0.08711 0.08429 0.0110 1.0000 0.0641
-9.000 -0.5534 0.08510 0.08234 0.0120 1.0000 0.0648
-8.750 -0.5540 0.08068 0.07797 0.0091 1.0000 0.0657
-8.500 -0.5705 0.07457 0.07186 0.0042 1.0000 0.0666
-8.250 -0.5901 0.06967 0.06692 0.0024 1.0000 0.0677
-8.000 -0.6547 0.06181 0.05833 0.0013 0.8968 0.0718
-7.750 -0.6417 0.05959 0.05604 0.0037 0.8219 0.0725
-7.500 -0.6961 0.04042 0.03485 0.0098 0.8220 0.0393
-7.250 -0.6888 0.03540 0.02917 0.0130 0.7898 0.0347
-7.000 -0.6726 0.03319 0.02655 0.0152 0.7598 0.0338
-6.750 -0.6540 0.03105 0.02408 0.0169 0.7330 0.0334
-6.500 -0.6337 0.02908 0.02173 0.0185 0.7095 0.0332
-6.250 -0.6118 0.02731 0.01959 0.0200 0.6876 0.0331
-6.000 -0.5882 0.02579 0.01772 0.0212 0.6670 0.0333
-5.750 -0.5633 0.02448 0.01610 0.0223 0.6472 0.0336
-5.500 -0.5380 0.02337 0.01470 0.0232 0.6281 0.0345
-5.250 -0.5120 0.02238 0.01371 0.0237 0.6096 0.0359
-5.000 -0.4857 0.02158 0.01280 0.0244 0.5920 0.0376
-4.750 -0.4590 0.02075 0.01176 0.0252 0.5755 0.0388
-4.500 -0.4332 0.01971 0.01073 0.0260 0.5604 0.0401
-4.000 -0.3826 0.01825 0.00914 0.0277 0.5309 0.0447
-3.750 -0.3580 0.01760 0.00849 0.0286 0.5172 0.0487
-3.500 -0.3336 0.01705 0.00788 0.0295 0.5051 0.0551
-3.250 -0.3094 0.01633 0.00724 0.0304 0.4920 0.0665
-3.000 -0.2870 0.01543 0.00653 0.0317 0.4808 0.1036
-2.750 -0.2672 0.01426 0.00608 0.0329 0.4694 0.2377
-2.500 -0.2456 0.01362 0.00584 0.0341 0.4585 0.3384
-2.250 -0.2262 0.01290 0.00562 0.0357 0.4485 0.4593
-2.000 -0.2095 0.01208 0.00553 0.0383 0.4392 0.6174
-1.750 -0.1819 0.01183 0.00593 0.0402 0.4287 0.7874
-1.500 -0.1491 0.01230 0.00640 0.0409 0.4179 0.8564
-1.250 -0.1172 0.01289 0.00683 0.0419 0.4081 0.8932
-1.000 -0.0702 0.01361 0.00741 0.0400 0.3969 0.9155
-0.750 -0.0225 0.01412 0.00765 0.0372 0.3871 0.9289
-0.500 0.0249 0.01441 0.00783 0.0342 0.3765 0.9395
-0.250 0.0747 0.01473 0.00788 0.0306 0.3675 0.9475
0.000 0.1157 0.01490 0.00799 0.0285 0.3591 0.9579
0.250 0.1665 0.01506 0.00793 0.0244 0.3512 0.9651
0.500 0.2140 0.01518 0.00796 0.0209 0.3430 0.9744
0.750 0.2639 0.01519 0.00783 0.0168 0.3354 0.9842
1.000 0.3158 0.01523 0.00771 0.0122 0.3289 0.9932
1.250 0.3647 0.01503 0.00747 0.0080 0.3219 1.0000
1.500 0.3882 0.01509 0.00743 0.0087 0.3172 1.0000
1.750 0.4118 0.01534 0.00751 0.0092 0.3128 1.0000
2.000 0.4360 0.01540 0.00763 0.0098 0.3085 1.0000
2.250 0.4601 0.01552 0.00773 0.0104 0.3041 1.0000
2.500 0.4841 0.01564 0.00777 0.0110 0.3000 1.0000
2.750 0.5081 0.01589 0.00789 0.0116 0.2963 1.0000
3.000 0.5324 0.01610 0.00813 0.0121 0.2924 1.0000
3.250 0.5567 0.01627 0.00833 0.0126 0.2883 1.0000
3.500 0.5810 0.01645 0.00848 0.0132 0.2846 1.0000
3.750 0.6051 0.01666 0.00861 0.0139 0.2814 1.0000
4.000 0.6291 0.01711 0.00894 0.0144 0.2780 1.0000
4.250 0.6532 0.01730 0.00925 0.0150 0.2746 1.0000
4.500 0.6770 0.01754 0.00953 0.0156 0.2709 1.0000
4.750 0.7007 0.01780 0.00978 0.0162 0.2676 1.0000
5.000 0.7242 0.01807 0.01000 0.0169 0.2648 1.0000
5.250 0.7476 0.01857 0.01039 0.0176 0.2620 1.0000
5.500 0.7705 0.01897 0.01090 0.0183 0.2590 1.0000
5.750 0.7932 0.01933 0.01135 0.0190 0.2557 1.0000
6.000 0.8159 0.01966 0.01171 0.0197 0.2525 1.0000
6.250 0.8386 0.01998 0.01201 0.0205 0.2499 1.0000
6.500 0.8613 0.02037 0.01235 0.0214 0.2475 1.0000
6.750 0.8832 0.02112 0.01305 0.0221 0.2449 1.0000
7.000 0.9040 0.02158 0.01368 0.0230 0.2423 1.0000
7.250 0.9246 0.02207 0.01428 0.0239 0.2393 1.0000
7.500 0.9454 0.02251 0.01478 0.0249 0.2365 1.0000
7.750 0.9666 0.02290 0.01517 0.0259 0.2341 1.0000
8.000 0.9881 0.02334 0.01556 0.0268 0.2320 1.0000
8.250 1.0091 0.02414 0.01629 0.0277 0.2298 1.0000
8.500 1.0262 0.02490 0.01724 0.0289 0.2276 1.0000
8.750 1.0429 0.02560 0.01810 0.0302 0.2250 1.0000
9.000 1.0602 0.02623 0.01884 0.0314 0.2223 1.0000
9.250 1.0783 0.02678 0.01944 0.0327 0.2201 1.0000
9.500 1.0978 0.02727 0.01993 0.0338 0.2181 1.0000
9.750 1.1186 0.02779 0.02041 0.0348 0.2163 1.0000
10.000 1.1377 0.02888 0.02146 0.0357 0.2143 1.0000
10.250 1.1471 0.02993 0.02278 0.0374 0.2122 1.0000
10.500 1.1577 0.03100 0.02404 0.0389 0.2096 1.0000
10.750 1.1706 0.03195 0.02511 0.0402 0.2074 1.0000
11.000 1.1856 0.03279 0.02602 0.0413 0.2054 1.0000
11.250 1.2039 0.03339 0.02663 0.0421 0.2035 1.0000
11.500 1.2274 0.03379 0.02697 0.0426 0.2018 1.0000
11.750 1.2470 0.03495 0.02811 0.0431 0.1998 1.0000
12.000 1.2380 0.03714 0.03064 0.0451 0.1978 1.0000
12.250 1.2212 0.03984 0.03361 0.0470 0.1957 1.0000
12.500 1.1709 0.04450 0.03852 0.0486 0.1939 1.0000
13.000 0.6996 0.12521 0.11982 0.0063 0.1733 1.0000
13.250 0.6872 0.13265 0.12731 0.0031 0.1732 1.0000
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Polar data table (+)
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