; This is a polar exchange file
; Comments start with a ';' in column 1
[Airfoil]
Airfoilname=MH 30  7.84%   
NumberSets=1

[Set1]
Origin=Eppler PROFIL (calculation)
Description1=Copyright 1996 Martin Hepperle
Description2=Created Sun May 26 12:03:59 1996

NumberPolars=5

[Set1-Polar1]
; the following line for compatibility with older versions
Re-Nr=100000
; future versions should use the following line
ReynoldsNumber=100000
MachNumber=0.00
Description1=
NumberPoints=9
;----  Alpha      Cl        Cd         Cm
Value01=0.00   -0.00   0.0112   -0.0409
Value02=1.00   0.11   0.0108   -0.0414
Value03=2.00   0.22   0.0108   -0.0423
Value04=3.00   0.33   0.0111   -0.0435
Value05=4.00   0.44   0.0118   -0.0451
Value06=5.00   0.55   0.0129   -0.0463
Value07=6.00   0.66   0.0148   -0.0472
Value08=7.00   0.76   0.0171   -0.0469
Value09=8.00   0.86   0.0189   -0.0453

[Set1-Polar2]
; 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   0.0085   -0.0414
Value02=1.00   0.11   0.0080   -0.0422
Value03=2.00   0.22   0.0079   -0.0432
Value04=3.00   0.33   0.0081   -0.0442
Value05=4.00   0.44   0.0089   -0.0453
Value06=5.00   0.55   0.0100   -0.0465
Value07=6.00   0.66   0.0119   -0.0478
Value08=7.00   0.77   0.0141   -0.0484
Value09=8.00   0.87   0.0161   -0.0474
Value10=9.00   0.96   0.0173   -0.0441

[Set1-Polar3]
; 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=-1.00   -0.11   0.0095   -0.0406
Value02=0.00   0.00   0.0066   -0.0414
Value03=1.00   0.11   0.0061   -0.0422
Value04=2.00   0.22   0.0060   -0.0432
Value05=3.00   0.33   0.0061   -0.0442
Value06=4.00   0.44   0.0069   -0.0453
Value07=5.00   0.55   0.0080   -0.0465
Value08=6.00   0.66   0.0097   -0.0478
Value09=7.00   0.77   0.0118   -0.0490
Value10=8.00   0.87   0.0138   -0.0491
Value11=9.00   0.97   0.0154   -0.0478

[Set1-Polar4]
; 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=-1.00   -0.11   0.0087   -0.0406
Value02=0.00   0.00   0.0059   -0.0414
Value03=1.00   0.11   0.0054   -0.0422
Value04=2.00   0.22   0.0053   -0.0432
Value05=3.00   0.33   0.0055   -0.0442
Value06=4.00   0.44   0.0061   -0.0453
Value07=5.00   0.55   0.0071   -0.0465
Value08=6.00   0.66   0.0087   -0.0478
Value09=7.00   0.77   0.0106   -0.0492
Value10=8.00   0.88   0.0127   -0.0498
Value11=9.00   0.98   0.0142   -0.0491
Value12=10.00   1.07   0.0158   -0.0461

[Set1-Polar5]
; 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=13
;----  Alpha      Cl        Cd         Cm
Value01=-1.00   -0.11   0.0079   -0.0406
Value02=0.00   0.00   0.0056   -0.0414
Value03=1.00   0.11   0.0051   -0.0422
Value04=2.00   0.22   0.0049   -0.0432
Value05=3.00   0.33   0.0053   -0.0442
Value06=4.00   0.44   0.0056   -0.0453
Value07=5.00   0.55   0.0064   -0.0465
Value08=6.00   0.66   0.0076   -0.0478
Value09=7.00   0.77   0.0095   -0.0492
Value10=8.00   0.88   0.0114   -0.0503
Value11=9.00   0.98   0.0128   -0.0505
Value12=10.00   1.08   0.0144   -0.0486
Value13=11.00   1.14   0.0161   -0.0405