; This is a polar exchange file ; Comments start with a ';' in column 1 [Airfoil] ; obsolete: Airfoilname=MH 43 ; new: Description1=MH 43 NumberSets=1 [Set1] Origin=Eppler PROFIL (calculation) Description1=Copyright 1996 Martin Hepperle Description2=Created Mon May 13 09:54:37 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=10 ;---- Alpha Cl Cd Cm Value01=-1.00 -0.11 0.0122 -0.0208 Value02=0.00 0.00 0.0114 -0.0215 Value03=1.00 0.11 0.0113 -0.0223 Value04=2.00 0.22 0.0114 -0.0232 Value05=3.00 0.33 0.0117 -0.0241 Value06=4.00 0.44 0.0122 -0.0252 Value07=5.00 0.55 0.0130 -0.0263 Value08=6.00 0.66 0.0145 -0.0274 Value09=7.00 0.76 0.0174 -0.0258 Value10=8.00 0.84 0.0193 -0.0204 [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=11 ;---- Alpha Cl Cd Cm Value01=-1.00 -0.11 0.0097 -0.0208 Value02=0.00 0.00 0.0088 -0.0215 Value03=1.00 0.11 0.0086 -0.0223 Value04=2.00 0.22 0.0086 -0.0232 Value05=3.00 0.33 0.0089 -0.0241 Value06=4.00 0.44 0.0094 -0.0252 Value07=5.00 0.55 0.0101 -0.0263 Value08=6.00 0.66 0.0113 -0.0276 Value09=7.00 0.77 0.0143 -0.0285 Value10=8.00 0.86 0.0165 -0.0250 Value11=9.00 0.93 0.0179 -0.0185 [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=14 ;---- Alpha Cl Cd Cm Value01=-2.00 -0.22 0.0105 -0.0201 Value02=-1.00 -0.11 0.0078 -0.0208 Value03=0.00 0.00 0.0069 -0.0215 Value04=1.00 0.11 0.0067 -0.0223 Value05=2.00 0.22 0.0067 -0.0232 Value06=3.00 0.33 0.0070 -0.0241 Value07=4.00 0.44 0.0074 -0.0252 Value08=5.00 0.55 0.0080 -0.0263 Value09=6.00 0.66 0.0091 -0.0276 Value10=7.00 0.77 0.0118 -0.0289 Value11=8.00 0.87 0.0141 -0.0284 Value12=9.00 0.96 0.0157 -0.0242 Value13=9.50 0.99 0.0165 -0.0206 Value14=10.00 1.01 0.0172 -0.0158 [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=16 ;---- Alpha Cl Cd Cm Value01=-2.00 -0.22 0.0097 -0.0201 Value02=-1.00 -0.11 0.0070 -0.0208 Value03=0.00 0.00 0.0062 -0.0215 Value04=1.00 0.11 0.0060 -0.0223 Value05=2.00 0.22 0.0060 -0.0232 Value06=3.00 0.33 0.0061 -0.0241 Value07=4.00 0.44 0.0064 -0.0252 Value08=5.00 0.55 0.0070 -0.0263 Value09=6.00 0.66 0.0081 -0.0276 Value10=7.00 0.77 0.0108 -0.0289 Value11=8.00 0.88 0.0130 -0.0296 Value12=9.00 0.97 0.0144 -0.0268 Value13=9.50 1.01 0.0152 -0.0239 Value14=10.00 1.04 0.0160 -0.0200 Value15=10.50 1.06 0.0169 -0.0151 Value16=11.00 1.04 0.0176 -0.0063 [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=18 ;---- Alpha Cl Cd Cm Value01=-3.00 -0.33 0.0093 -0.0196 Value02=-2.00 -0.22 0.0089 -0.0201 Value03=-1.00 -0.11 0.0069 -0.0208 Value04=0.00 0.00 0.0059 -0.0215 Value05=1.00 0.11 0.0056 -0.0223 Value06=2.00 0.22 0.0055 -0.0232 Value07=3.00 0.33 0.0055 -0.0241 Value08=4.00 0.44 0.0057 -0.0252 Value09=5.00 0.55 0.0062 -0.0263 Value10=6.00 0.66 0.0073 -0.0276 Value11=7.00 0.77 0.0096 -0.0289 Value12=8.00 0.88 0.0117 -0.0302 Value13=9.00 0.98 0.0130 -0.0296 Value14=9.50 1.02 0.0137 -0.0276 Value15=10.00 1.06 0.0145 -0.0245 Value16=10.50 1.09 0.0153 -0.0205 Value17=11.00 1.11 0.0162 -0.0154 Value18=12.00 1.11 0.0182 -0.0028