; This is a polar exchange file
; Comments start with a ';' in column 1
[Airfoil]
; obsolete:
Airfoilname=MH 22
; new:
Description1=MH 22
NumberSets=1

[Set1]
Origin=Eppler PROFIL (calculation)
Description1=Copyright 1996 Martin Hepperle
Description2=Created Mon May 13 11:43:24 1996

NumberPolars=5

[Set1-Polar1]
; the following line for compatibility with older versions
Re-Nr=200000
; future versions should use the following line
ReynoldsNumber=200000
MachNumber=0.00
Description1=
NumberPoints=10
;----  Alpha      Cl        Cd         Cm
Value01=0.00   0.00   0.0082   -0.0146
Value02=0.50   0.06   0.0082   -0.0148
Value03=1.00   0.11   0.0083   -0.0150
Value04=1.50   0.17   0.0083   -0.0153
Value05=2.00   0.22   0.0084   -0.0156
Value06=3.00   0.33   0.0087   -0.0163
Value07=4.00   0.44   0.0096   -0.0171
Value08=5.00   0.55   0.0105   -0.0181
Value09=6.00   0.66   0.0117   -0.0193
Value10=7.00   0.77   0.0149   -0.0200

[Set1-Polar2]
; the following line for compatibility with older versions
Re-Nr=400000
; future versions should use the following line
ReynoldsNumber=400000
MachNumber=0.00
Description1=
NumberPoints=11
;----  Alpha      Cl        Cd         Cm
Value01=0.00   0.00   0.0063   -0.0144
Value02=0.50   0.06   0.0063   -0.0147
Value03=1.00   0.11   0.0064   -0.0150
Value04=1.50   0.17   0.0064   -0.0153
Value05=2.00   0.22   0.0065   -0.0156
Value06=3.00   0.33   0.0068   -0.0163
Value07=4.00   0.44   0.0076   -0.0171
Value08=5.00   0.55   0.0085   -0.0181
Value09=6.00   0.66   0.0095   -0.0193
Value10=7.00   0.77   0.0127   -0.0205
Value11=8.00   0.88   0.0140   -0.0207

[Set1-Polar3]
; the following line for compatibility with older versions
Re-Nr=600000
; future versions should use the following line
ReynoldsNumber=600000
MachNumber=0.00
Description1=
NumberPoints=12
;----  Alpha      Cl        Cd         Cm
Value01=-1.50   -0.17   0.0095   -0.0131
Value02=0.00   0.00   0.0054   -0.0142
Value03=0.50   0.06   0.0055   -0.0145
Value04=1.00   0.11   0.0055   -0.0148
Value05=1.50   0.17   0.0056   -0.0151
Value06=2.00   0.22   0.0056   -0.0155
Value07=3.00   0.33   0.0059   -0.0162
Value08=4.00   0.44   0.0067   -0.0171
Value09=5.00   0.55   0.0075   -0.0181
Value10=6.00   0.66   0.0085   -0.0193
Value11=7.00   0.77   0.0116   -0.0205
Value12=8.00   0.88   0.0129   -0.0213

[Set1-Polar4]
; the following line for compatibility with older versions
Re-Nr=1000000
; future versions should use the following line
ReynoldsNumber=1000000
MachNumber=0.00
Description1=
NumberPoints=14
;----  Alpha      Cl        Cd         Cm
Value01=-2.00   -0.22   0.0089   -0.0128
Value02=-1.50   -0.17   0.0087   -0.0131
Value03=0.00   0.00   0.0047   -0.0139
Value04=0.50   0.06   0.0046   -0.0142
Value05=1.00   0.11   0.0047   -0.0145
Value06=1.50   0.17   0.0048   -0.0149
Value07=2.00   0.22   0.0049   -0.0153
Value08=3.00   0.33   0.0052   -0.0161
Value09=4.00   0.44   0.0060   -0.0171
Value10=5.00   0.55   0.0066   -0.0181
Value11=6.00   0.66   0.0074   -0.0193
Value12=7.00   0.77   0.0105   -0.0205
Value13=8.00   0.88   0.0116   -0.0218
Value14=9.00   0.98   0.0129   -0.0217

[Set1-Polar5]
; the following line for compatibility with older versions
Re-Nr=2000000
; future versions should use the following line
ReynoldsNumber=2000000
MachNumber=0.00
Description1=
NumberPoints=16
;----  Alpha      Cl        Cd         Cm
Value01=-3.00   -0.33   0.0084   -0.0125
Value02=-2.00   -0.22   0.0080   -0.0128
Value03=-1.50   -0.17   0.0078   -0.0131
Value04=0.00   0.00   0.0050   -0.0139
Value05=0.50   0.06   0.0045   -0.0142
Value06=1.00   0.11   0.0041   -0.0145
Value07=1.50   0.17   0.0041   -0.0149
Value08=2.00   0.22   0.0044   -0.0153
Value09=3.00   0.33   0.0049   -0.0161
Value10=4.00   0.44   0.0054   -0.0171
Value11=5.00   0.55   0.0060   -0.0181
Value12=6.00   0.66   0.0067   -0.0193
Value13=7.00   0.77   0.0092   -0.0205
Value14=8.00   0.88   0.0101   -0.0218
Value15=9.00   0.99   0.0113   -0.0229
Value16=10.00   1.09   0.0127   -0.0221