; This is a polar exchange file ; Comments start with a ';' in column 1 [Airfoil] ; obsolete: Airfoilname=MH 26 ; new: Description1=MH 26 NumberSets=1 [Set1] Origin=Eppler PROFIL (calculation) Description1=Copyright 1996 Martin Hepperle Description2=Created Mon May 13 12:50:04 1996 NumberPolars=5 [Set1-Polar1] ; 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=-1.00 -0.16 0.0122 -0.0206 Value02=-0.50 -0.08 0.0087 -0.0274 Value03=0.00 -0.03 0.0086 -0.0273 Value04=1.00 0.07 0.0086 -0.0273 Value05=2.00 0.17 0.0087 -0.0274 Value06=3.00 0.27 0.0089 -0.0283 Value07=4.00 0.39 0.0093 -0.0329 Value08=4.50 0.45 0.0096 -0.0350 Value09=5.00 0.51 0.0101 -0.0378 Value10=5.50 0.57 0.0108 -0.0394 Value11=6.00 0.62 0.0118 -0.0405 Value12=7.00 0.72 0.0153 -0.0411 Value13=8.00 0.82 0.0181 -0.0409 [Set1-Polar2] ; 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=13 ;---- Alpha Cl Cd Cm Value01=-1.00 -0.15 0.0102 -0.0220 Value02=-0.50 -0.08 0.0063 -0.0270 Value03=0.00 -0.03 0.0063 -0.0272 Value04=1.00 0.07 0.0063 -0.0276 Value05=2.00 0.17 0.0063 -0.0281 Value06=3.00 0.28 0.0065 -0.0305 Value07=4.00 0.41 0.0068 -0.0356 Value08=4.50 0.46 0.0071 -0.0375 Value09=5.00 0.52 0.0076 -0.0394 Value10=5.50 0.58 0.0083 -0.0406 Value11=6.00 0.63 0.0094 -0.0413 Value12=7.00 0.73 0.0127 -0.0417 Value13=8.00 0.82 0.0156 -0.0419 [Set1-Polar3] ; 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=-1.50 -0.19 0.0095 -0.0233 Value02=-1.00 -0.14 0.0092 -0.0238 Value03=-0.50 -0.07 0.0052 -0.0275 Value04=0.00 -0.02 0.0052 -0.0279 Value05=1.00 0.08 0.0052 -0.0288 Value06=2.00 0.18 0.0053 -0.0297 Value07=3.00 0.31 0.0055 -0.0350 Value08=4.00 0.42 0.0059 -0.0381 Value09=4.50 0.47 0.0064 -0.0395 Value10=5.00 0.53 0.0069 -0.0404 Value11=5.50 0.58 0.0076 -0.0411 Value12=6.00 0.63 0.0084 -0.0416 Value13=7.00 0.73 0.0115 -0.0420 Value14=8.00 0.83 0.0143 -0.0424 [Set1-Polar4] ; 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=15 ;---- Alpha Cl Cd Cm Value01=-2.00 -0.23 0.0087 -0.0257 Value02=-1.50 -0.18 0.0085 -0.0263 Value03=-1.00 -0.12 0.0082 -0.0269 Value04=-0.50 -0.07 0.0042 -0.0288 Value05=0.00 -0.01 0.0042 -0.0294 Value06=1.00 0.09 0.0042 -0.0306 Value07=2.00 0.21 0.0044 -0.0343 Value08=3.00 0.32 0.0047 -0.0367 Value09=4.00 0.42 0.0055 -0.0387 Value10=4.50 0.47 0.0060 -0.0394 Value11=5.00 0.53 0.0065 -0.0401 Value12=5.50 0.58 0.0072 -0.0408 Value13=6.00 0.63 0.0080 -0.0415 Value14=7.00 0.73 0.0102 -0.0423 Value15=8.00 0.83 0.0129 -0.0428 [Set1-Polar5] ; the following line for compatibility with older versions Re-Nr=2000000 ; future versions should use the following line ReynoldsNumber=2000000 MachNumber=0.00 Description1= NumberPoints=16 ;---- Alpha Cl Cd Cm Value01=-3.00 -0.33 0.0082 -0.0266 Value02=-2.00 -0.22 0.0076 -0.0278 Value03=-1.50 -0.17 0.0073 -0.0285 Value04=-1.00 -0.11 0.0071 -0.0293 Value05=-0.50 -0.06 0.0039 -0.0294 Value06=0.00 -0.01 0.0035 -0.0306 Value07=1.00 0.10 0.0035 -0.0330 Value08=2.00 0.21 0.0039 -0.0350 Value09=3.00 0.32 0.0046 -0.0367 Value10=4.00 0.42 0.0055 -0.0384 Value11=4.50 0.47 0.0059 -0.0392 Value12=5.00 0.53 0.0064 -0.0401 Value13=5.50 0.58 0.0070 -0.0410 Value14=6.00 0.63 0.0077 -0.0418 Value15=7.00 0.74 0.0092 -0.0434 Value16=8.00 0.84 0.0114 -0.0442