; This is a polar exchange file
; Comments start with a ';' in column 1
[Airfoil]
Airfoilname=MH 34
NumberSets=1

[Set1]
Origin=Eppler PROFIL (calculation)
Description1=Copyright 1997 Martin Hepperle
Description2=Created Sat Jan 11 21:19:00 1997

NumberPolars=5

[Set1-Polar1]
; the following line for compatibility with older versions
Re-Nr=60000
; future versions should use the following line
ReynoldsNumber=60000
MachNumber=0.00
Description1=
NumberPoints=11
;----  Alpha      Cl        Cd         Cm
Value01=-1.00   -0.12   0.0143   -0.0291
Value02=-0.50   -0.06   0.0140   -0.0312
Value03=0.00   -0.00   0.0139   -0.0321
Value04=0.50   0.05   0.0139   -0.0320
Value05=1.00   0.10   0.0139   -0.0318
Value06=2.00   0.21   0.0141   -0.0326
Value07=3.00   0.32   0.0146   -0.0339
Value08=4.00   0.43   0.0155   -0.0353
Value09=5.00   0.54   0.0173   -0.0359
Value10=6.00   0.64   0.0193   -0.0360
Value11=7.00   0.75   0.0210   -0.0357

[Set1-Polar2]
; 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=12
;----  Alpha      Cl        Cd         Cm
Value01=-1.00   -0.12   0.0113   -0.0285
Value02=-0.50   -0.06   0.0110   -0.0310
Value03=0.00   0.00   0.0109   -0.0323
Value04=0.50   0.05   0.0109   -0.0324
Value05=1.00   0.10   0.0109   -0.0324
Value06=2.00   0.22   0.0111   -0.0338
Value07=3.00   0.33   0.0116   -0.0352
Value08=4.00   0.44   0.0125   -0.0364
Value09=5.00   0.54   0.0144   -0.0368
Value10=6.00   0.65   0.0166   -0.0369
Value11=7.00   0.75   0.0184   -0.0366
Value12=8.00   0.85   0.0198   -0.0354

[Set1-Polar3]
; 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=13
;----  Alpha      Cl        Cd         Cm
Value01=-2.00   -0.23   0.0116   -0.0276
Value02=-1.00   -0.12   0.0083   -0.0285
Value03=-0.50   -0.06   0.0080   -0.0307
Value04=0.00   0.00   0.0079   -0.0326
Value05=0.50   0.06   0.0078   -0.0331
Value06=1.00   0.11   0.0079   -0.0333
Value07=2.00   0.22   0.0081   -0.0351
Value08=3.00   0.33   0.0086   -0.0364
Value09=4.00   0.44   0.0096   -0.0373
Value10=5.00   0.55   0.0115   -0.0377
Value11=6.00   0.65   0.0136   -0.0379
Value12=7.00   0.76   0.0155   -0.0377
Value13=8.00   0.86   0.0170   -0.0371

[Set1-Polar4]
; 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=14
;----  Alpha      Cl        Cd         Cm
Value01=-2.00   -0.23   0.0099   -0.0287
Value02=-1.00   -0.12   0.0063   -0.0298
Value03=-0.50   -0.06   0.0058   -0.0304
Value04=0.00   0.00   0.0057   -0.0324
Value05=0.50   0.06   0.0057   -0.0334
Value06=1.00   0.11   0.0057   -0.0339
Value07=2.00   0.22   0.0060   -0.0354
Value08=3.00   0.33   0.0065   -0.0366
Value09=4.00   0.44   0.0075   -0.0375
Value10=5.00   0.55   0.0093   -0.0382
Value11=6.00   0.66   0.0114   -0.0387
Value12=7.00   0.76   0.0132   -0.0387
Value13=8.00   0.86   0.0146   -0.0384
Value14=9.00   0.96   0.0161   -0.0373

[Set1-Polar5]
; 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=14
;----  Alpha      Cl        Cd         Cm
Value01=-2.00   -0.22   0.0091   -0.0296
Value02=-1.00   -0.11   0.0057   -0.0308
Value03=-0.50   -0.06   0.0053   -0.0315
Value04=0.00   -0.00   0.0049   -0.0322
Value05=0.50   0.05   0.0048   -0.0328
Value06=1.00   0.11   0.0049   -0.0336
Value07=2.00   0.22   0.0052   -0.0348
Value08=3.00   0.33   0.0057   -0.0360
Value09=4.00   0.44   0.0066   -0.0373
Value10=5.00   0.55   0.0083   -0.0384
Value11=6.00   0.66   0.0103   -0.0392
Value12=7.00   0.76   0.0120   -0.0393
Value13=8.00   0.87   0.0134   -0.0392
Value14=9.00   0.97   0.0148   -0.0383