MH 45 9.85% (mh45-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 45 9.85% (mh45-il) Reynolds number: 100,000 Max Cl/Cd: 45.9 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh45-il-100000-n5.txt Download as CSV file: xf-mh45-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 45 9.85%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5728 0.09158 0.08708 0.0065 1.0000 0.0168
-9.000 -0.5767 0.08578 0.08135 0.0028 1.0000 0.0172
-8.750 -0.6101 0.06755 0.06309 -0.0121 1.0000 0.0144
-8.500 -0.6200 0.06239 0.05788 -0.0165 1.0000 0.0142
-8.250 -0.6295 0.05703 0.05232 -0.0197 1.0000 0.0141
-8.000 -0.6331 0.05198 0.04700 -0.0217 1.0000 0.0140
-7.750 -0.6307 0.04737 0.04203 -0.0229 1.0000 0.0140
-7.500 -0.6245 0.04280 0.03688 -0.0234 1.0000 0.0143
-7.250 -0.6127 0.03930 0.03312 -0.0237 1.0000 0.0150
-7.000 -0.5952 0.03703 0.03064 -0.0239 1.0000 0.0159
-6.750 -0.5766 0.03444 0.02771 -0.0238 1.0000 0.0168
-6.500 -0.5565 0.03174 0.02459 -0.0236 1.0000 0.0176
-6.250 -0.5347 0.02913 0.02156 -0.0232 1.0000 0.0181
-6.000 -0.5117 0.02687 0.01895 -0.0228 1.0000 0.0186
-5.750 -0.4883 0.02498 0.01678 -0.0223 0.9974 0.0192
-5.500 -0.4545 0.02316 0.01468 -0.0236 0.9701 0.0202
-5.250 -0.4240 0.02143 0.01286 -0.0246 0.9522 0.0220
-5.000 -0.3940 0.02043 0.01172 -0.0252 0.9364 0.0257
-4.750 -0.3678 0.01929 0.01045 -0.0250 0.9217 0.0299
-4.500 -0.3425 0.01842 0.00939 -0.0243 0.9081 0.0365
-4.250 -0.3194 0.01736 0.00835 -0.0233 0.8954 0.0524
-4.000 -0.2982 0.01605 0.00748 -0.0222 0.8837 0.1241
-3.750 -0.2759 0.01534 0.00711 -0.0213 0.8726 0.2174
-3.500 -0.2527 0.01488 0.00687 -0.0204 0.8612 0.2896
-3.250 -0.2296 0.01449 0.00667 -0.0194 0.8505 0.3574
-3.000 -0.2060 0.01418 0.00642 -0.0183 0.8405 0.4080
-2.750 -0.1819 0.01391 0.00620 -0.0172 0.8306 0.4551
-2.500 -0.1572 0.01364 0.00600 -0.0162 0.8202 0.5041
-2.250 -0.1327 0.01338 0.00583 -0.0151 0.8105 0.5567
-2.000 -0.1083 0.01312 0.00566 -0.0139 0.8013 0.6146
-1.750 -0.0831 0.01286 0.00555 -0.0128 0.7907 0.6793
-1.500 -0.0570 0.01262 0.00546 -0.0116 0.7810 0.7520
-1.250 -0.0241 0.01244 0.00537 -0.0115 0.7721 0.8314
-1.000 0.0222 0.01235 0.00524 -0.0145 0.7612 0.9027
-0.750 0.0683 0.01232 0.00508 -0.0177 0.7505 0.9523
-0.500 0.1129 0.01230 0.00489 -0.0208 0.7399 0.9870
-0.250 0.1451 0.01230 0.00473 -0.0217 0.7292 1.0000
0.000 0.1693 0.01234 0.00465 -0.0210 0.7172 1.0000
0.250 0.1936 0.01238 0.00459 -0.0203 0.7054 1.0000
0.500 0.2179 0.01244 0.00452 -0.0195 0.6935 1.0000
0.750 0.2424 0.01249 0.00448 -0.0187 0.6816 1.0000
1.000 0.2670 0.01255 0.00444 -0.0179 0.6695 1.0000
1.250 0.2918 0.01262 0.00442 -0.0172 0.6567 1.0000
1.500 0.3169 0.01269 0.00443 -0.0165 0.6431 1.0000
1.750 0.3421 0.01278 0.00444 -0.0158 0.6290 1.0000
2.000 0.3673 0.01287 0.00447 -0.0152 0.6145 1.0000
2.250 0.3926 0.01297 0.00452 -0.0145 0.5995 1.0000
2.500 0.4181 0.01308 0.00458 -0.0139 0.5838 1.0000
2.750 0.4437 0.01321 0.00466 -0.0133 0.5670 1.0000
3.000 0.4693 0.01335 0.00476 -0.0128 0.5497 1.0000
3.250 0.4948 0.01351 0.00490 -0.0122 0.5321 1.0000
3.500 0.5203 0.01369 0.00501 -0.0116 0.5143 1.0000
3.750 0.5459 0.01389 0.00518 -0.0111 0.4953 1.0000
4.000 0.5714 0.01411 0.00538 -0.0106 0.4757 1.0000
4.250 0.5967 0.01436 0.00558 -0.0101 0.4564 1.0000
4.500 0.6222 0.01463 0.00583 -0.0096 0.4360 1.0000
4.750 0.6474 0.01493 0.00609 -0.0091 0.4155 1.0000
5.000 0.6726 0.01525 0.00642 -0.0087 0.3950 1.0000
5.250 0.6976 0.01560 0.00675 -0.0083 0.3738 1.0000
5.500 0.7224 0.01599 0.00712 -0.0078 0.3529 1.0000
5.750 0.7470 0.01640 0.00752 -0.0074 0.3310 1.0000
6.000 0.7714 0.01684 0.00798 -0.0070 0.3094 1.0000
6.250 0.7955 0.01733 0.00846 -0.0066 0.2871 1.0000
6.500 0.8192 0.01785 0.00898 -0.0061 0.2652 1.0000
6.750 0.8425 0.01843 0.00954 -0.0057 0.2434 1.0000
7.000 0.8655 0.01904 0.01019 -0.0052 0.2226 1.0000
7.250 0.8878 0.01972 0.01086 -0.0047 0.2028 1.0000
7.500 0.9096 0.02047 0.01159 -0.0042 0.1850 1.0000
7.750 0.9312 0.02122 0.01239 -0.0036 0.1683 1.0000
8.000 0.9521 0.02204 0.01324 -0.0030 0.1530 1.0000
8.250 0.9724 0.02291 0.01418 -0.0023 0.1396 1.0000
8.500 0.9919 0.02384 0.01515 -0.0016 0.1273 1.0000
8.750 1.0103 0.02484 0.01618 -0.0009 0.1162 1.0000
9.000 1.0285 0.02584 0.01728 -0.0001 0.1060 1.0000
9.250 1.0460 0.02690 0.01845 0.0008 0.0963 1.0000
9.500 1.0615 0.02808 0.01969 0.0017 0.0882 1.0000
9.750 1.0761 0.02927 0.02097 0.0027 0.0803 1.0000
10.000 1.0898 0.03055 0.02243 0.0038 0.0729 1.0000
10.250 1.1002 0.03196 0.02388 0.0050 0.0672 1.0000
10.500 1.1110 0.03340 0.02551 0.0062 0.0611 1.0000
10.750 1.1162 0.03491 0.02709 0.0077 0.0565 1.0000
11.000 1.1197 0.03672 0.02901 0.0091 0.0528 1.0000
11.250 1.1240 0.03856 0.03103 0.0102 0.0487 1.0000
11.500 1.1255 0.04063 0.03319 0.0108 0.0456 1.0000
11.750 1.1255 0.04311 0.03572 0.0114 0.0431 1.0000
12.000 1.1274 0.04566 0.03853 0.0118 0.0407 1.0000
12.250 1.1270 0.04843 0.04148 0.0118 0.0384 1.0000
12.500 1.1251 0.05139 0.04457 0.0115 0.0365 1.0000
12.750 1.1207 0.05469 0.04793 0.0106 0.0348 1.0000
13.000 1.1161 0.05832 0.05172 0.0098 0.0334 1.0000
13.250 1.1093 0.06252 0.05620 0.0084 0.0322 1.0000
13.500 1.1010 0.06712 0.06103 0.0067 0.0312 1.0000
13.750 1.0905 0.07225 0.06638 0.0044 0.0304 1.0000
14.000 1.0781 0.07788 0.07221 0.0017 0.0299 1.0000
14.250 1.0637 0.08414 0.07865 -0.0017 0.0295 1.0000
14.500 1.0463 0.09136 0.08606 -0.0058 0.0292 1.0000
14.750 1.0249 0.09993 0.09482 -0.0108 0.0293 1.0000
15.000 0.9968 0.11060 0.10563 -0.0173 0.0299 1.0000
15.250 0.9597 0.12442 0.11959 -0.0255 0.0309 1.0000
15.500 0.9136 0.14224 0.13744 -0.0353 0.0323 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 45 9.85% (mh45-il)