; This is a polar exchange file ; Comments start with a ';' in column 1 [Airfoil] Airfoilname=MH 31 NumberSets=1 [Set1] Origin=Eppler PROFIL (calculation) Description1=Copyright 1997 Martin Hepperle Description2=Created Sat Jan 11 21:16:28 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=14 ;---- Alpha Cl Cd Cm Value01=-2.00 -0.23 0.0159 -0.0145 Value02=-1.50 -0.17 0.0150 -0.0145 Value03=-1.00 -0.12 0.0141 -0.0147 Value04=-0.50 -0.06 0.0137 -0.0151 Value05=0.00 -0.01 0.0135 -0.0159 Value06=0.50 0.05 0.0135 -0.0168 Value07=1.00 0.11 0.0136 -0.0174 Value08=1.50 0.16 0.0138 -0.0179 Value09=2.00 0.22 0.0140 -0.0185 Value10=3.00 0.33 0.0149 -0.0195 Value11=4.00 0.44 0.0163 -0.0199 Value12=5.00 0.54 0.0178 -0.0197 Value13=6.00 0.65 0.0192 -0.0189 Value14=7.00 0.74 0.0209 -0.0164 [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=15 ;---- Alpha Cl Cd Cm Value01=-2.00 -0.22 0.0138 -0.0150 Value02=-1.50 -0.17 0.0125 -0.0151 Value03=-1.00 -0.12 0.0112 -0.0154 Value04=-0.50 -0.06 0.0108 -0.0157 Value05=0.00 -0.00 0.0107 -0.0167 Value06=0.50 0.06 0.0106 -0.0177 Value07=1.00 0.11 0.0107 -0.0184 Value08=1.50 0.17 0.0109 -0.0189 Value09=2.00 0.22 0.0111 -0.0193 Value10=3.00 0.33 0.0121 -0.0199 Value11=4.00 0.44 0.0136 -0.0203 Value12=5.00 0.55 0.0150 -0.0204 Value13=6.00 0.65 0.0165 -0.0202 Value14=7.00 0.75 0.0180 -0.0190 Value15=8.00 0.84 0.0199 -0.0152 [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=16 ;---- Alpha Cl Cd Cm Value01=-2.00 -0.22 0.0115 -0.0156 Value02=-1.50 -0.17 0.0099 -0.0159 Value03=-1.00 -0.11 0.0085 -0.0163 Value04=-0.50 -0.06 0.0079 -0.0166 Value05=0.00 0.00 0.0077 -0.0174 Value06=0.50 0.06 0.0077 -0.0183 Value07=1.00 0.11 0.0078 -0.0190 Value08=1.50 0.17 0.0079 -0.0192 Value09=2.00 0.22 0.0082 -0.0195 Value10=3.00 0.33 0.0093 -0.0200 Value11=4.00 0.44 0.0108 -0.0205 Value12=5.00 0.55 0.0122 -0.0209 Value13=6.00 0.66 0.0135 -0.0211 Value14=7.00 0.76 0.0150 -0.0207 Value15=8.00 0.86 0.0166 -0.0191 Value16=9.00 0.94 0.0186 -0.0139 [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=16 ;---- Alpha Cl Cd Cm Value01=-2.00 -0.22 0.0097 -0.0160 Value02=-1.50 -0.17 0.0079 -0.0163 Value03=-1.00 -0.11 0.0066 -0.0167 Value04=-0.50 -0.06 0.0059 -0.0170 Value05=0.00 0.00 0.0056 -0.0173 Value06=0.50 0.06 0.0057 -0.0180 Value07=1.00 0.11 0.0058 -0.0188 Value08=1.50 0.17 0.0060 -0.0191 Value09=2.00 0.22 0.0063 -0.0194 Value10=3.00 0.33 0.0073 -0.0200 Value11=4.00 0.44 0.0087 -0.0205 Value12=5.00 0.55 0.0100 -0.0211 Value13=6.00 0.66 0.0113 -0.0217 Value14=7.00 0.77 0.0126 -0.0218 Value15=8.00 0.87 0.0140 -0.0210 Value16=9.00 0.96 0.0158 -0.0184 [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=16 ;---- Alpha Cl Cd Cm Value01=-2.00 -0.22 0.0089 -0.0160 Value02=-1.50 -0.17 0.0071 -0.0163 Value03=-1.00 -0.11 0.0060 -0.0167 Value04=-0.50 -0.06 0.0055 -0.0170 Value05=0.00 0.00 0.0052 -0.0173 Value06=0.50 0.06 0.0051 -0.0177 Value07=1.00 0.11 0.0051 -0.0182 Value08=1.50 0.17 0.0053 -0.0189 Value09=2.00 0.22 0.0056 -0.0192 Value10=3.00 0.33 0.0065 -0.0199 Value11=4.00 0.44 0.0078 -0.0205 Value12=5.00 0.55 0.0090 -0.0211 Value13=6.00 0.66 0.0102 -0.0219 Value14=7.00 0.77 0.0114 -0.0223 Value15=8.00 0.87 0.0128 -0.0218 Value16=9.00 0.97 0.0144 -0.0200