; This is a polar exchange file
; Comments start with a ';' in column 1
[Airfoil]
Airfoilname=MH 116  9.84%  
NumberSets=1

[Set1]
Origin=Eppler PROFIL (calculation)
Description1=Copyright 1997 Martin Hepperle
Description2=Created Mon Mar 10 20:24:01 1997
Description3=Rough Surface

NumberPolars=3

[Set1-Polar1]
; the following line for compatibility with older versions
Re-Nr=300000
; future versions should use the following line
ReynoldsNumber=300000
MachNumber=0.5
Description1=
NumberPoints=13
;----  Alpha      Cl        Cd         Cm
Value01=-5.00   -0.11   0.0129   -0.1353
Value02=-4.00   0.03   0.0122   -0.1374
Value03=-3.00   0.18   0.0117   -0.1399
Value04=-2.00   0.32   0.0113   -0.1423
Value05=-1.00   0.47   0.0111   -0.1447
Value06=0.00   0.61   0.0112   -0.1471
Value07=1.00   0.75   0.0114   -0.1494
Value08=2.00   0.89   0.0121   -0.1514
Value09=3.00   1.02   0.0138   -0.1529
Value10=4.00   1.15   0.0160   -0.1533
Value11=5.00   1.27   0.0188   -0.1512
Value12=6.00   1.36   0.0223   -0.1457
Value13=7.00   1.44   0.0263   -0.1401

[Set1-Polar2]
; the following line for compatibility with older versions
Re-Nr=500000
; future versions should use the following line
ReynoldsNumber=500000
MachNumber=0.5
Description1=
NumberPoints=13
;----  Alpha      Cl        Cd         Cm
Value01=-5.00   -0.11   0.0118   -0.1348
Value02=-4.00   0.03   0.0110   -0.1374
Value03=-3.00   0.18   0.0106   -0.1401
Value04=-2.00   0.32   0.0102   -0.1427
Value05=-1.00   0.47   0.0102   -0.1452
Value06=0.00   0.61   0.0103   -0.1477
Value07=1.00   0.75   0.0107   -0.1500
Value08=2.00   0.89   0.0117   -0.1520
Value09=3.00   1.03   0.0131   -0.1536
Value10=4.00   1.16   0.0150   -0.1546
Value11=5.00   1.28   0.0175   -0.1538
Value12=6.00   1.38   0.0204   -0.1492
Value13=7.00   1.47   0.0239   -0.1437

[Set1-Polar3]
; the following line for compatibility with older versions
Re-Nr=700000
; future versions should use the following line
ReynoldsNumber=700000
MachNumber=0.5
Description1=
NumberPoints=13
;----  Alpha      Cl        Cd         Cm
Value01=-5.00   -0.11   0.0112   -0.1348
Value02=-4.00   0.03   0.0105   -0.1374
Value03=-3.00   0.18   0.0100   -0.1401
Value04=-2.00   0.32   0.0098   -0.1428
Value05=-1.00   0.47   0.0097   -0.1454
Value06=0.00   0.61   0.0099   -0.1479
Value07=1.00   0.75   0.0106   -0.1502
Value08=2.00   0.89   0.0116   -0.1524
Value09=3.00   1.03   0.0129   -0.1540
Value10=4.00   1.16   0.0146   -0.1553
Value11=5.00   1.28   0.0168   -0.1548
Value12=6.00   1.39   0.0195   -0.1514
Value13=7.00   1.48   0.0226   -0.1460