MH 32

Designed for electric powered pylon racing model aircraft (FAI class F5D).
Can also be used for F3B and F3J sailplane models (Model «Cygnus»).

Characteristics

Calculated Polars (PROFIL/Eppler):

Calculated Polars (X-Foil/Drela):

Experimental Polars (University of Stuttgart):

Comments on Experimental Polars (UIUC and Stuttgart)

Coordinates

     x         y
    1.00000   0.00000
    0.99904   0.00008
    0.99620   0.00033
    0.99153   0.00082
    0.98510   0.00156
    0.97697   0.00259
    0.96721   0.00389
    0.95589   0.00548
    0.94309   0.00734
    0.92888   0.00946
    0.91335   0.01182
    0.89657   0.01439
    0.87861   0.01714
    0.85955   0.02006
    0.83949   0.02311
    0.81849   0.02623
    0.79662   0.02940
    0.77397   0.03259
    0.75063   0.03575
    0.72662   0.03879
    0.70199   0.04174
    0.67682   0.04459
    0.65119   0.04730
    0.62516   0.04983
    0.59878   0.05221
    0.57214   0.05443
    0.54534   0.05649
    0.51846   0.05837
    0.49159   0.06006
    0.46484   0.06153
    0.43826   0.06273
    0.41190   0.06366
    0.38584   0.06433
    0.36016   0.06474
    0.33494   0.06488
    0.31027   0.06473
    0.28619   0.06425
    0.26273   0.06347
    0.23996   0.06240
    0.21796   0.06106
    0.19679   0.05945
    0.17652   0.05756
    0.15719   0.05536
    0.13881   0.05290
    0.12145   0.05019
    0.10515   0.04724
    0.08993   0.04405
    0.07582   0.04066
    0.06287   0.03710
    0.05111   0.03337
    0.04052   0.02950
    0.03112   0.02554
    0.02295   0.02154
    0.01602   0.01751
    0.01030   0.01350
    0.00580   0.00963
    0.00255   0.00597
    0.00061   0.00262
    0.00002   0.00044
    0.00000  -0.00020
    0.00010  -0.00078
    0.00035  -0.00132
    0.00076  -0.00187
    0.00131  -0.00245
    0.00448  -0.00475
    0.00921  -0.00706
    0.01544  -0.00929
    0.02314  -0.01139
    0.03232  -0.01336
    0.04292  -0.01519
    0.05491  -0.01683
    0.06828  -0.01828
    0.08302  -0.01956
    0.09904  -0.02064
    0.11634  -0.02152
    0.13487  -0.02221
    0.15459  -0.02271
    0.17542  -0.02304
    0.19732  -0.02317
    0.22023  -0.02314
    0.24409  -0.02296
    0.26881  -0.02264
    0.29432  -0.02218
    0.32055  -0.02160
    0.34741  -0.02092
    0.37481  -0.02015
    0.40266  -0.01928
    0.43089  -0.01835
    0.45939  -0.01736
    0.48806  -0.01632
    0.51682  -0.01524
    0.54558  -0.01413
    0.57423  -0.01301
    0.60268  -0.01188
    0.63083  -0.01075
    0.65860  -0.00965
    0.68588  -0.00857
    0.71258  -0.00753
    0.73861  -0.00654
    0.76387  -0.00560
    0.78828  -0.00472
    0.81174  -0.00391
    0.83418  -0.00317
    0.85551  -0.00251
    0.87564  -0.00194
    0.89450  -0.00145
    0.91202  -0.00105
    0.92811  -0.00073
    0.94272  -0.00048
    0.95577  -0.00030
    0.96723  -0.00017
    0.97703  -0.00009
    0.98513  -0.00002
    0.99153   0.00003
    0.99619   0.00005
    0.99904   0.00002
    1.00000   0.00000
This airfoil has originally been published in [3].

last modification of this page: 15.12.00

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Copyright 1986-2001 Martin Hepperle
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