MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: MH 27 11.99% (mh27-il) Reynolds number: 200,000 Max Cl/Cd: 69.88 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh27-il-200000.txt Download as CSV file: xf-mh27-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 27 11.99%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5590 0.09011 0.08694 -0.0361 1.0000 0.0386
-8.750 -0.5788 0.08575 0.08257 -0.0370 1.0000 0.0384
-8.500 -0.6026 0.08231 0.07911 -0.0354 1.0000 0.0382
-8.250 -0.6298 0.07975 0.07652 -0.0313 1.0000 0.0381
-8.000 -0.6528 0.07749 0.07423 -0.0268 1.0000 0.0379
-7.750 -0.6709 0.07445 0.07110 -0.0231 1.0000 0.0384
-7.500 -0.6901 0.07136 0.06778 -0.0186 1.0000 0.0400
-7.250 -0.7032 0.07008 0.06618 -0.0135 1.0000 0.0409
-7.000 -0.7128 0.06807 0.06391 -0.0088 1.0000 0.0412
-6.750 -0.7306 0.06153 0.05719 -0.0047 1.0000 0.0420
-6.500 -0.7281 0.05724 0.05297 -0.0027 1.0000 0.0431
-6.250 -0.7247 0.05466 0.05035 0.0000 1.0000 0.0442
-6.000 -0.7210 0.05227 0.04787 0.0029 1.0000 0.0457
-5.750 -0.7172 0.04978 0.04521 0.0062 1.0000 0.0480
-5.250 -0.7118 0.04430 0.03899 0.0141 1.0000 0.0562
-5.000 -0.7010 0.04207 0.03672 0.0163 1.0000 0.0582
-4.750 -0.6903 0.04004 0.03449 0.0192 1.0000 0.0619
-4.500 -0.6672 0.03115 0.02393 0.0276 1.0000 0.0208
-4.250 -0.6494 0.02897 0.02155 0.0296 1.0000 0.0193
-3.750 -0.5639 0.02464 0.01639 0.0249 0.9875 0.0189
-3.500 -0.5236 0.02372 0.01530 0.0227 0.9837 0.0194
-3.250 -0.4957 0.02244 0.01402 0.0224 0.9765 0.0243
-3.000 -0.4608 0.02188 0.01339 0.0211 0.9723 0.0287
-2.750 -0.4371 0.02079 0.01225 0.0222 0.9652 0.0392
-2.500 -0.4171 0.01898 0.01156 0.0233 0.9603 0.2353
-2.250 -0.3032 0.01964 0.01501 0.0086 0.9717 0.9355
-2.000 -0.2129 0.02116 0.01623 -0.0034 0.9738 0.9611
-1.750 -0.1373 0.02185 0.01668 -0.0132 0.9743 0.9747
-1.500 -0.0532 0.02229 0.01692 -0.0252 0.9761 0.9903
-1.250 0.0159 0.02244 0.01692 -0.0344 0.9764 1.0000
-1.000 0.0579 0.02252 0.01690 -0.0382 0.9718 1.0000
-0.750 0.0874 0.02230 0.01662 -0.0393 0.9636 1.0000
-0.500 0.1292 0.02232 0.01657 -0.0429 0.9590 1.0000
-0.250 0.1576 0.02212 0.01632 -0.0437 0.9506 1.0000
0.000 0.2000 0.02205 0.01622 -0.0472 0.9460 1.0000
0.250 0.2284 0.02184 0.01599 -0.0478 0.9375 1.0000
0.500 0.2714 0.02167 0.01579 -0.0514 0.9328 1.0000
0.750 0.3004 0.02142 0.01555 -0.0520 0.9243 1.0000
1.000 0.3438 0.02113 0.01527 -0.0555 0.9196 1.0000
1.250 0.3735 0.02082 0.01498 -0.0561 0.9110 1.0000
1.500 0.4178 0.02040 0.01459 -0.0595 0.9064 1.0000
1.750 0.4472 0.02001 0.01424 -0.0600 0.8976 1.0000
2.000 0.4930 0.01945 0.01376 -0.0636 0.8930 1.0000
2.250 0.5215 0.01897 0.01333 -0.0636 0.8835 1.0000
2.500 0.5699 0.01821 0.01266 -0.0675 0.8791 1.0000
2.750 0.5969 0.01761 0.01214 -0.0671 0.8681 1.0000
3.000 0.6278 0.01694 0.01158 -0.0674 0.8581 1.0000
3.250 0.6734 0.01590 0.01065 -0.0703 0.8516 1.0000
3.500 0.6886 0.01536 0.01018 -0.0672 0.8351 1.0000
3.750 0.7101 0.01476 0.00969 -0.0654 0.8160 1.0000
4.000 0.7537 0.01388 0.00890 -0.0679 0.7927 1.0000
4.250 0.8569 0.01257 0.00751 -0.0826 0.7242 1.0000
4.500 0.8903 0.01274 0.00729 -0.0834 0.6383 1.0000
4.750 0.8997 0.01327 0.00748 -0.0795 0.5689 1.0000
5.000 0.9045 0.01387 0.00778 -0.0748 0.5076 1.0000
5.250 0.9077 0.01448 0.00812 -0.0699 0.4505 1.0000
5.500 0.9107 0.01510 0.00848 -0.0651 0.3965 1.0000
5.750 0.9139 0.01571 0.00887 -0.0604 0.3465 1.0000
6.000 0.9177 0.01632 0.00928 -0.0559 0.3009 1.0000
6.250 0.9207 0.01696 0.00970 -0.0512 0.2556 1.0000
6.500 0.9230 0.01757 0.01013 -0.0465 0.2150 1.0000
6.750 0.9256 0.01821 0.01059 -0.0418 0.1769 1.0000
7.000 0.9284 0.01890 0.01114 -0.0373 0.1426 1.0000
7.250 0.9318 0.01965 0.01174 -0.0329 0.1126 1.0000
7.500 0.9339 0.02051 0.01246 -0.0283 0.0899 1.0000
7.750 0.9366 0.02140 0.01330 -0.0237 0.0719 1.0000
8.000 0.9393 0.02231 0.01420 -0.0192 0.0606 1.0000
8.250 0.9408 0.02338 0.01523 -0.0146 0.0530 1.0000
8.500 0.9479 0.02414 0.01609 -0.0110 0.0470 1.0000
8.750 0.9518 0.02582 0.01772 -0.0071 0.0423 1.0000
9.000 0.9617 0.02649 0.01857 -0.0039 0.0386 1.0000
9.250 0.9692 0.02730 0.01943 -0.0006 0.0347 1.0000
9.500 0.9860 0.02965 0.02186 0.0009 0.0306 1.0000
9.750 0.9892 0.03013 0.02251 0.0051 0.0270 1.0000
10.000 0.9966 0.03134 0.02380 0.0082 0.0243 1.0000
10.250 1.0069 0.03403 0.02671 0.0105 0.0208 1.0000
10.500 1.0085 0.03491 0.02780 0.0146 0.0187 1.0000
10.750 1.0121 0.03648 0.02956 0.0182 0.0171 1.0000
11.000 1.0147 0.03852 0.03183 0.0217 0.0165 1.0000
11.250 1.0138 0.04039 0.03389 0.0256 0.0159 1.0000
11.500 1.0093 0.04262 0.03630 0.0295 0.0152 1.0000
11.750 1.0030 0.04496 0.03888 0.0336 0.0151 1.0000
12.000 0.9922 0.04765 0.04180 0.0377 0.0149 1.0000
12.250 0.9769 0.05072 0.04512 0.0419 0.0147 1.0000
12.500 0.9612 0.05365 0.04829 0.0457 0.0147 1.0000
12.750 0.9450 0.05658 0.05146 0.0488 0.0149 1.0000
13.000 0.9259 0.06008 0.05517 0.0513 0.0148 1.0000
13.250 0.9065 0.06377 0.05911 0.0530 0.0151 1.0000
13.500 0.8830 0.06845 0.06402 0.0537 0.0153 1.0000
13.750 0.8555 0.07439 0.07022 0.0529 0.0158 1.0000
14.000 0.8269 0.08119 0.07724 0.0505 0.0161 1.0000
14.250 0.7936 0.09020 0.08646 0.0457 0.0166 1.0000
14.500 0.7632 0.10033 0.09674 0.0395 0.0170 1.0000
14.750 0.7260 0.11432 0.11083 0.0314 0.0186 1.0000
15.000 0.6986 0.12667 0.12312 0.0258 0.0200 1.0000
15.250 0.6802 0.13682 0.13321 0.0219 0.0204 1.0000
15.500 0.6717 0.14288 0.13923 0.0200 0.0213 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 27 11.99% (mh27-il)