MH 110 10.01% (mh110-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 110 10.01% (mh110-il) Reynolds number: 200,000 Max Cl/Cd: 55.96 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh110-il-200000-n5.txt Download as CSV file: xf-mh110-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 110 10.01%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6896 0.08046 0.07727 0.0133 1.0000 0.0077
-9.500 -0.7043 0.06956 0.06633 0.0045 1.0000 0.0075
-9.250 -0.7254 0.06225 0.05889 -0.0013 1.0000 0.0075
-9.000 -0.7446 0.05764 0.05414 -0.0021 1.0000 0.0074
-8.750 -0.7624 0.05354 0.04985 -0.0005 1.0000 0.0074
-8.500 -0.7727 0.04920 0.04525 0.0009 1.0000 0.0073
-8.250 -0.7771 0.04497 0.04069 0.0026 1.0000 0.0072
-8.000 -0.7764 0.04096 0.03631 0.0045 1.0000 0.0071
-7.750 -0.7714 0.03716 0.03209 0.0065 1.0000 0.0071
-7.500 -0.7619 0.03376 0.02826 0.0084 1.0000 0.0070
-7.250 -0.7484 0.03084 0.02492 0.0102 1.0000 0.0070
-7.000 -0.7320 0.02825 0.02194 0.0119 1.0000 0.0070
-6.750 -0.7132 0.02595 0.01928 0.0134 1.0000 0.0070
-6.500 -0.6926 0.02399 0.01702 0.0147 1.0000 0.0071
-6.250 -0.6709 0.02230 0.01510 0.0158 1.0000 0.0072
-6.000 -0.6487 0.02082 0.01344 0.0170 1.0000 0.0074
-5.750 -0.6262 0.01953 0.01196 0.0181 1.0000 0.0076
-5.500 -0.6036 0.01844 0.01074 0.0192 1.0000 0.0079
-5.250 -0.5830 0.01708 0.00929 0.0205 1.0000 0.0086
-5.000 -0.5603 0.01621 0.00835 0.0215 1.0000 0.0094
-4.750 -0.5365 0.01557 0.00766 0.0223 1.0000 0.0113
-4.500 -0.5131 0.01485 0.00687 0.0232 1.0000 0.0142
-4.250 -0.4895 0.01416 0.00613 0.0242 1.0000 0.0194
-4.000 -0.4532 0.01311 0.00526 0.0223 0.9136 0.0582
-3.750 -0.4242 0.01236 0.00477 0.0220 0.8362 0.1356
-3.500 -0.4034 0.01182 0.00443 0.0235 0.7837 0.2150
-3.250 -0.3819 0.01141 0.00412 0.0248 0.7418 0.2816
-3.000 -0.3603 0.01103 0.00384 0.0261 0.7060 0.3507
-2.750 -0.3386 0.01066 0.00360 0.0275 0.6746 0.4245
-2.500 -0.3169 0.01031 0.00336 0.0289 0.6460 0.4974
-2.250 -0.2952 0.00998 0.00318 0.0304 0.6200 0.5703
-2.000 -0.2731 0.00968 0.00305 0.0319 0.5957 0.6450
-1.750 -0.2494 0.00946 0.00297 0.0332 0.5730 0.7152
-1.500 -0.2223 0.00934 0.00292 0.0340 0.5511 0.7775
-1.250 -0.1898 0.00935 0.00290 0.0336 0.5291 0.8282
-1.000 -0.1518 0.00947 0.00292 0.0320 0.5076 0.8650
-0.750 -0.1129 0.00962 0.00294 0.0301 0.4869 0.8911
-0.500 -0.0755 0.00979 0.00295 0.0285 0.4680 0.9104
-0.250 -0.0397 0.00995 0.00297 0.0271 0.4501 0.9263
0.000 -0.0023 0.01012 0.00300 0.0253 0.4329 0.9386
0.250 0.0346 0.01029 0.00303 0.0236 0.4174 0.9485
0.500 0.0699 0.01045 0.00306 0.0222 0.4027 0.9582
0.750 0.1048 0.01060 0.00309 0.0208 0.3883 0.9670
1.000 0.1424 0.01072 0.00310 0.0188 0.3744 0.9733
1.250 0.1771 0.01084 0.00313 0.0174 0.3623 0.9805
1.500 0.2145 0.01093 0.00312 0.0153 0.3509 0.9856
1.750 0.2511 0.01103 0.00315 0.0134 0.3401 0.9912
2.000 0.2883 0.01110 0.00316 0.0113 0.3291 0.9961
2.250 0.3238 0.01117 0.00317 0.0095 0.3192 1.0000
2.500 0.3478 0.01127 0.00322 0.0101 0.3118 1.0000
2.750 0.3721 0.01136 0.00331 0.0108 0.3046 1.0000
3.000 0.3962 0.01150 0.00340 0.0114 0.2984 1.0000
3.250 0.4206 0.01161 0.00353 0.0120 0.2917 1.0000
3.500 0.4448 0.01178 0.00364 0.0127 0.2857 1.0000
3.750 0.4692 0.01191 0.00383 0.0133 0.2795 1.0000
4.000 0.4935 0.01208 0.00399 0.0139 0.2742 1.0000
4.250 0.5178 0.01228 0.00419 0.0146 0.2697 1.0000
4.500 0.5423 0.01246 0.00442 0.0152 0.2648 1.0000
4.750 0.5667 0.01267 0.00466 0.0158 0.2602 1.0000
5.000 0.5910 0.01290 0.00491 0.0164 0.2559 1.0000
5.250 0.6155 0.01311 0.00520 0.0170 0.2511 1.0000
5.500 0.6398 0.01335 0.00549 0.0177 0.2473 1.0000
5.750 0.6639 0.01365 0.00579 0.0183 0.2438 1.0000
6.000 0.6885 0.01389 0.00618 0.0189 0.2394 1.0000
6.250 0.7128 0.01415 0.00653 0.0196 0.2350 1.0000
6.500 0.7368 0.01445 0.00686 0.0202 0.2309 1.0000
6.750 0.7611 0.01468 0.00724 0.0208 0.2247 1.0000
7.000 0.7849 0.01491 0.00751 0.0215 0.2172 1.0000
7.250 0.8092 0.01508 0.00783 0.0221 0.2073 1.0000
7.500 0.8332 0.01528 0.00817 0.0227 0.1961 1.0000
7.750 0.8570 0.01551 0.00850 0.0233 0.1839 1.0000
8.000 0.8806 0.01579 0.00888 0.0239 0.1706 1.0000
8.250 0.9037 0.01615 0.00929 0.0245 0.1496 1.0000
8.500 0.9228 0.01711 0.00999 0.0252 0.0976 1.0000
8.750 0.9378 0.01872 0.01136 0.0262 0.0550 1.0000
9.000 0.9537 0.02012 0.01270 0.0272 0.0341 1.0000
9.250 0.9697 0.02141 0.01404 0.0283 0.0233 1.0000
9.500 0.9841 0.02280 0.01551 0.0296 0.0167 1.0000
9.750 0.9962 0.02432 0.01719 0.0308 0.0126 1.0000
10.000 1.0073 0.02583 0.01889 0.0322 0.0109 1.0000
10.250 1.0180 0.02724 0.02044 0.0335 0.0091 1.0000
10.500 1.0252 0.02884 0.02215 0.0348 0.0078 1.0000
10.750 1.0255 0.03092 0.02437 0.0362 0.0067 1.0000
11.000 1.0211 0.03301 0.02663 0.0379 0.0064 1.0000
11.250 1.0114 0.03605 0.02982 0.0376 0.0063 1.0000
11.500 1.0044 0.03991 0.03383 0.0355 0.0063 1.0000
11.750 0.9954 0.04441 0.03848 0.0330 0.0063 1.0000
12.000 0.9869 0.04892 0.04312 0.0306 0.0059 1.0000
12.250 0.9778 0.05347 0.04778 0.0284 0.0059 1.0000
12.500 0.9686 0.05807 0.05248 0.0263 0.0056 1.0000
12.750 0.9599 0.06256 0.05707 0.0243 0.0055 1.0000
13.000 0.9527 0.06683 0.06144 0.0225 0.0057 1.0000
13.250 0.9430 0.07165 0.06635 0.0203 0.0053 1.0000
13.500 0.9374 0.07572 0.07052 0.0187 0.0055 1.0000
13.750 0.9275 0.08083 0.07570 0.0163 0.0050 1.0000
14.000 0.9230 0.08505 0.08002 0.0146 0.0051 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 110 10.01% (mh110-il)