; This is a polar exchange file
; Comments start with a ';' in column 1
[Airfoil]
Airfoilname=MH 108
NumberSets=2

[Set1]
Origin=Eppler PROFIL (calculation)
Description1=smooth surface
Description2=Created Sat Mar 08 19:40:59 1997
Description3=Copyright 1997 Martin Hepperle
NumberPolars=3

[Set1-Polar1]
; the following line for compatibility with older versions
Re-Nr=500000
; future versions should use the following line
ReynoldsNumber=500000
MachNumber=0.00
Description1=smooth surface
NumberPoints=13
;----  Alpha      Cl        Cd         Cm
Value01=-4.00   -0.44   0.0109   0.0261
Value02=-3.00   -0.33   0.0100   0.0252
Value03=-2.00   -0.22   0.0092   0.0242
Value04=-1.00   -0.11   0.0082   0.0231
Value05=0.00   0.00   0.0081   0.0221
Value06=1.00   0.11   0.0081   0.0209
Value07=2.00   0.22   0.0082   0.0197
Value08=4.00   0.44   0.0088   0.0170
Value09=5.50   0.60   0.0096   0.0155
Value10=6.00   0.66   0.0099   0.0153
Value11=6.50   0.71   0.0103   0.0153
Value12=8.00   0.86   0.0130   0.0180
Value13=10.00   0.82   0.0190   0.0444

[Set1-Polar2]
; the following line for compatibility with older versions
Re-Nr=700000
; future versions should use the following line
ReynoldsNumber=700000
MachNumber=0.00
Description1=smooth surface
NumberPoints=14
;----  Alpha      Cl        Cd         Cm
Value01=-4.00   -0.44   0.0100   0.0261
Value02=-3.00   -0.33   0.0093   0.0252
Value03=-2.00   -0.22   0.0085   0.0242
Value04=-1.00   -0.11   0.0079   0.0231
Value05=0.00   0.00   0.0076   0.0221
Value06=1.00   0.11   0.0075   0.0209
Value07=2.00   0.22   0.0076   0.0198
Value08=4.00   0.44   0.0080   0.0173
Value09=5.50   0.61   0.0087   0.0153
Value10=6.00   0.66   0.0090   0.0149
Value11=6.50   0.71   0.0094   0.0147
Value12=8.00   0.86   0.0119   0.0164
Value13=10.00   0.85   0.0177   0.0438
Value14=12.00   0.89   0.0224   0.0455

[Set1-Polar3]
; the following line for compatibility with older versions
Re-Nr=1000000
; future versions should use the following line
ReynoldsNumber=1000000
MachNumber=0.00
Description1=smooth surface
NumberPoints=14
;----  Alpha      Cl        Cd         Cm
Value01=-4.00   -0.44   0.0094   0.0261
Value02=-3.00   -0.33   0.0087   0.0252
Value03=-2.00   -0.22   0.0081   0.0242
Value04=-1.00   -0.11   0.0077   0.0231
Value05=0.00   0.00   0.0072   0.0221
Value06=1.00   0.11   0.0071   0.0209
Value07=2.00   0.22   0.0071   0.0198
Value08=4.00   0.44   0.0074   0.0174
Value09=5.50   0.61   0.0079   0.0154
Value10=6.00   0.66   0.0081   0.0148
Value11=6.50   0.71   0.0085   0.0143
Value12=8.00   0.87   0.0108   0.0153
Value13=10.00   0.88   0.0165   0.0427
Value14=12.00   0.91   0.0209   0.0468

[Set2]
Origin=Eppler PROFIL (calculation)
Description1=rough surface (r=3)
Description2=Created Sat Mar 08 19:40:59 1997
Description3=Copyright 1997 Martin Hepperle
NumberPolars=3


[Set2-Polar1]
; the following line for compatibility with older versions
Re-Nr=500000
; future versions should use the following line
ReynoldsNumber=500000
MachNumber=0.00
Description1=rogh surface (r=3)
NumberPoints=13
;----  Alpha      Cl        Cd         Cm
Value01=-4.00   -0.44   0.0118   0.0261
Value02=-3.00   -0.33   0.0112   0.0252
Value03=-2.00   -0.22   0.0109   0.0242
Value04=-1.00   -0.11   0.0106   0.0231
Value05=0.00   0.00   0.0103   0.0221
Value06=1.00   0.11   0.0101   0.0209
Value07=2.00   0.22   0.0100   0.0198
Value08=4.00   0.44   0.0098   0.0174
Value09=5.50   0.60   0.0107   0.0162
Value10=6.00   0.65   0.0112   0.0161
Value11=6.50   0.71   0.0117   0.0163
Value12=8.00   0.84   0.0138   0.0205
Value13=10.00   0.82   0.0190   0.0452

[Set2-Polar2]
; the following line for compatibility with older versions
Re-Nr=700000
; future versions should use the following line
ReynoldsNumber=700000
MachNumber=0.00
Description1=rough surface (r=3)
NumberPoints=14
;----  Alpha      Cl        Cd         Cm
Value01=-4.00   -0.44   0.0112   0.0261
Value02=-3.00   -0.33   0.0108   0.0252
Value03=-2.00   -0.22   0.0105   0.0242
Value04=-1.00   -0.11   0.0102   0.0231
Value05=0.00   0.00   0.0099   0.0221
Value06=1.00   0.11   0.0097   0.0209
Value07=2.00   0.22   0.0097   0.0198
Value08=4.00   0.44   0.0095   0.0174
Value09=5.50   0.60   0.0104   0.0159
Value10=6.00   0.66   0.0108   0.0159
Value11=6.50   0.71   0.0113   0.0159
Value12=8.00   0.85   0.0131   0.0189
Value13=10.00   0.85   0.0178   0.0445
Value14=12.00   0.89   0.0224   0.0463

[Set2-Polar3]
; the following line for compatibility with older versions
Re-Nr=1000000
; future versions should use the following line
ReynoldsNumber=1000000
MachNumber=0.00
Description1=rough surface (r=3)
NumberPoints=14
;----  Alpha      Cl        Cd         Cm
Value01=-4.00   -0.44   0.0107   0.0261
Value02=-3.00   -0.33   0.0103   0.0252
Value03=-2.00   -0.22   0.0100   0.0242
Value04=-1.00   -0.11   0.0097   0.0231
Value05=0.00   0.00   0.0095   0.0221
Value06=1.00   0.11   0.0094   0.0209
Value07=2.00   0.22   0.0093   0.0198
Value08=4.00   0.44   0.0096   0.0174
Value09=5.50   0.60   0.0102   0.0157
Value10=6.00   0.66   0.0106   0.0156
Value11=6.50   0.71   0.0110   0.0156
Value12=8.00   0.86   0.0126   0.0174
Value13=10.00   0.88   0.0167   0.0430
Value14=12.00   0.91   0.0209   0.0472