; This is a polar exchange file
; Comments start with a ';' in column 1
[Airfoil]
Airfoilname=MH 102
NumberSets=2

[Set1]
Origin=Eppler PROFIL (calculation)
Description1=smooth surface (r=0)
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=
NumberPoints=12
;----  Alpha      Cl        Cd         Cm
Value01=-3.00   -0.33   0.0111   -0.0561
Value02=-2.00   -0.22   0.0107   -0.0575
Value03=0.00   -0.00   0.0105   -0.0605
Value04=2.00   0.22   0.0107   -0.0633
Value05=4.00   0.43   0.0108   -0.0660
Value06=6.00   0.64   0.0104   -0.0682
Value07=8.00   0.85   0.0112   -0.0696
Value08=10.00   1.04   0.0136   -0.0662
Value09=12.00   1.14   0.0169   -0.0498
Value10=14.00   1.22   0.0212   -0.0374
Value11=16.00   1.28   0.0269   -0.0307
Value12=17.00   1.30   0.0304   -0.0294

[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=
NumberPoints=12
;----  Alpha      Cl        Cd         Cm
Value01=-3.00   -0.33   0.0103   -0.0560
Value02=-2.00   -0.22   0.0099   -0.0575
Value03=0.00   -0.00   0.0097   -0.0607
Value04=2.00   0.22   0.0099   -0.0636
Value05=4.00   0.43   0.0099   -0.0664
Value06=6.00   0.65   0.0095   -0.0689
Value07=8.00   0.86   0.0102   -0.0706
Value08=10.00   1.05   0.0124   -0.0690
Value09=12.00   1.17   0.0155   -0.0547
Value10=14.00   1.25   0.0195   -0.0404
Value11=16.00   1.31   0.0249   -0.0318
Value12=17.00   1.34   0.0281   -0.0298

[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=
NumberPoints=12
;----  Alpha      Cl        Cd         Cm
Value01=-3.00   -0.33   0.0096   -0.0559
Value02=-2.00   -0.22   0.0092   -0.0574
Value03=0.00   0.00   0.0091   -0.0608
Value04=2.00   0.22   0.0092   -0.0639
Value05=4.00   0.43   0.0091   -0.0668
Value06=6.00   0.65   0.0089   -0.0694
Value07=8.00   0.86   0.0095   -0.0714
Value08=10.00   1.06   0.0115   -0.0710
Value09=12.00   1.20   0.0142   -0.0601
Value10=14.00   1.29   0.0179   -0.0440
Value11=16.00   1.35   0.0229   -0.0335
Value12=17.00   1.38   0.0260   -0.0305

[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=
NumberPoints=12
;----  Alpha      Cl        Cd         Cm
Value01=-3.00   -0.33   0.0120   -0.0562
Value02=-2.00   -0.22   0.0117   -0.0576
Value03=0.00   -0.00   0.0112   -0.0603
Value04=2.00   0.21   0.0113   -0.0631
Value05=4.00   0.43   0.0117   -0.0657
Value06=6.00   0.64   0.0125   -0.0675
Value07=8.00   0.84   0.0139   -0.0676
Value08=10.00   1.00   0.0159   -0.0584
Value09=12.00   1.10   0.0189   -0.0444
Value10=14.00   1.18   0.0231   -0.0346
Value11=16.00   1.25   0.0287   -0.0298
Value12=17.00   1.28   0.0321   -0.0292

[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=
NumberPoints=12
;----  Alpha      Cl        Cd         Cm
Value01=-3.00   -0.33   0.0115   -0.0561
Value02=-2.00   -0.22   0.0110   -0.0575
Value03=0.00   -0.00   0.0106   -0.0605
Value04=2.00   0.22   0.0107   -0.0634
Value05=4.00   0.43   0.0110   -0.0661
Value06=6.00   0.64   0.0120   -0.0679
Value07=8.00   0.85   0.0135   -0.0686
Value08=10.00   1.01   0.0153   -0.0614
Value09=12.00   1.12   0.0181   -0.0467
Value10=14.00   1.20   0.0220   -0.0361
Value11=16.00   1.27   0.0272   -0.0302
Value12=17.00   1.30   0.0304   -0.0291

[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=
NumberPoints=12
;----  Alpha      Cl        Cd         Cm
Value01=-3.00   -0.33   0.0110   -0.0560
Value02=-2.00   -0.22   0.0104   -0.0574
Value03=0.00   -0.00   0.0101   -0.0607
Value04=2.00   0.22   0.0101   -0.0636
Value05=4.00   0.43   0.0107   -0.0662
Value06=6.00   0.64   0.0116   -0.0682
Value07=8.00   0.85   0.0130   -0.0692
Value08=10.00   1.03   0.0148   -0.0641
Value09=12.00   1.13   0.0174   -0.0492
Value10=14.00   1.22   0.0210   -0.0377
Value11=16.00   1.29   0.0259   -0.0309
Value12=17.00   1.33   0.0289   -0.0293