; This is a polar exchange file ; Comments start with a ';' in column 1 [Airfoil] Airfoilname=MH 104 NumberSets=2 [Set1] Origin=Eppler PROFIL (calculation) Description1=smooth surface (r=0) Description2=Created Sat Mar 08 19:40:59 1997 Description3=Copyright 1997 Martin Hepperle NumberPolars=3 [Set1-Polar1] ; the following line for compatibility with older versions Re-Nr=500000 ; future versions should use the following line ReynoldsNumber=500000 MachNumber=0.00 Description1= NumberPoints=14 ;---- Alpha Cl Cd Cm Value01=-4.00 -0.44 0.0130 0.0154 Value02=-2.00 -0.22 0.0102 0.0129 Value03=-1.00 -0.11 0.0098 0.0114 Value04=0.00 0.00 0.0094 0.0097 Value05=2.00 0.22 0.0083 0.0061 Value06=3.00 0.33 0.0084 0.0045 Value07=4.00 0.44 0.0086 0.0031 Value08=5.00 0.54 0.0090 0.0020 Value09=6.00 0.64 0.0096 0.0012 Value10=7.00 0.74 0.0101 0.0015 Value11=8.00 0.83 0.0109 0.0047 Value12=10.00 0.92 0.0144 0.0187 Value13=12.00 0.98 0.0206 0.0256 Value14=14.00 1.04 0.0294 0.0244 [Set1-Polar2] ; the following line for compatibility with older versions Re-Nr=700000 ; future versions should use the following line ReynoldsNumber=700000 MachNumber=0.00 Description1= NumberPoints=14 ;---- Alpha Cl Cd Cm Value01=-4.00 -0.44 0.0122 0.0155 Value02=-2.00 -0.22 0.0095 0.0130 Value03=-1.00 -0.11 0.0090 0.0114 Value04=0.00 0.00 0.0087 0.0097 Value05=2.00 0.22 0.0077 0.0060 Value06=3.00 0.33 0.0077 0.0042 Value07=4.00 0.44 0.0078 0.0027 Value08=5.00 0.54 0.0082 0.0013 Value09=6.00 0.65 0.0086 0.0003 Value10=7.00 0.75 0.0091 -0.0004 Value11=8.00 0.85 0.0098 0.0003 Value12=10.00 0.95 0.0132 0.0155 Value13=12.00 1.00 0.0191 0.0251 Value14=14.00 1.06 0.0275 0.0251 [Set1-Polar3] ; 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=14 ;---- Alpha Cl Cd Cm Value01=-4.00 -0.44 0.0115 0.0156 Value02=-2.00 -0.22 0.0087 0.0130 Value03=-1.00 -0.11 0.0084 0.0114 Value04=0.00 0.00 0.0082 0.0097 Value05=2.00 0.22 0.0073 0.0060 Value06=3.00 0.33 0.0071 0.0040 Value07=4.00 0.44 0.0072 0.0022 Value08=5.00 0.55 0.0074 0.0008 Value09=6.00 0.65 0.0078 -0.0005 Value10=7.00 0.76 0.0083 -0.0014 Value11=8.00 0.86 0.0091 -0.0015 Value12=10.00 0.98 0.0121 0.0120 Value13=12.00 1.03 0.0176 0.0245 Value14=14.00 1.08 0.0256 0.0260 [Set2] Origin=Eppler PROFIL (calculation) Description1=rough surface (r=3) Description2=Created Sat Mar 08 19:40:59 1997 Description3=Copyright 1997 Martin Hepperle NumberPolars=3 [Set2-Polar1] ; the following line for compatibility with older versions Re-Nr=500000 ; future versions should use the following line ReynoldsNumber=500000 MachNumber=0.00 Description1= NumberPoints=14 ;---- Alpha Cl Cd Cm Value01=-4.00 -0.44 0.0134 0.0154 Value02=-2.00 -0.22 0.0110 0.0129 Value03=-1.00 -0.11 0.0107 0.0114 Value04=0.00 0.00 0.0104 0.0097 Value05=2.00 0.22 0.0103 0.0062 Value06=3.00 0.33 0.0103 0.0048 Value07=4.00 0.43 0.0104 0.0035 Value08=5.00 0.54 0.0105 0.0027 Value09=6.00 0.64 0.0112 0.0027 Value10=7.00 0.72 0.0121 0.0060 Value11=8.00 0.78 0.0132 0.0133 Value12=10.00 0.87 0.0168 0.0234 Value13=12.00 0.96 0.0222 0.0267 Value14=14.00 1.04 0.0294 0.0252 [Set2-Polar2] ; the following line for compatibility with older versions Re-Nr=700000 ; future versions should use the following line ReynoldsNumber=700000 MachNumber=0.00 Description1= NumberPoints=14 ;---- Alpha Cl Cd Cm Value01=-4.00 -0.44 0.0127 0.0155 Value02=-2.00 -0.22 0.0104 0.0130 Value03=-1.00 -0.11 0.0101 0.0114 Value04=0.00 0.00 0.0099 0.0097 Value05=2.00 0.22 0.0098 0.0060 Value06=3.00 0.33 0.0098 0.0044 Value07=4.00 0.44 0.0100 0.0031 Value08=5.00 0.54 0.0104 0.0023 Value09=6.00 0.64 0.0110 0.0021 Value10=7.00 0.73 0.0118 0.0040 Value11=8.00 0.79 0.0129 0.0117 Value12=10.00 0.89 0.0160 0.0225 Value13=12.00 0.97 0.0210 0.0267 Value14=14.00 1.06 0.0275 0.0260 [Set2-Polar3] ; 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=14 ;---- Alpha Cl Cd Cm Value01=-4.00 -0.44 0.0120 0.0156 Value02=-2.00 -0.22 0.0099 0.0130 Value03=-1.00 -0.11 0.0096 0.0114 Value04=0.00 0.00 0.0095 0.0097 Value05=2.00 0.22 0.0093 0.0060 Value06=3.00 0.33 0.0094 0.0042 Value07=4.00 0.44 0.0098 0.0029 Value08=5.00 0.54 0.0103 0.0020 Value09=6.00 0.64 0.0108 0.0017 Value10=7.00 0.74 0.0116 0.0033 Value11=8.00 0.80 0.0127 0.0104 Value12=10.00 0.90 0.0154 0.0213 Value13=12.00 0.99 0.0202 0.0265 Value14=14.00 1.08 0.0257 0.0264