; This is a polar exchange file ; Comments start with a ';' in column 1 [Airfoil] ; obsolete: Airfoilname=MH 23 ; new: Description1=MH 23 NumberSets=1 [Set1] Origin=Eppler PROFIL (calculation) Description1=Copyright 1996 Martin Hepperle Description2=Created Mon May 13 12:28:04 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=12 ;---- Alpha Cl Cd Cm Value01=-1.00 -0.13 0.0111 -0.0109 Value02=-0.50 -0.07 0.0078 -0.0132 Value03=0.00 -0.02 0.0078 -0.0133 Value04=1.00 0.08 0.0077 -0.0135 Value05=2.00 0.20 0.0079 -0.0155 Value06=3.00 0.32 0.0083 -0.0189 Value07=4.00 0.44 0.0091 -0.0225 Value08=4.50 0.49 0.0098 -0.0235 Value09=5.00 0.54 0.0110 -0.0238 Value10=5.50 0.59 0.0126 -0.0234 Value11=6.00 0.64 0.0141 -0.0229 Value12=7.00 0.74 0.0156 -0.0222 [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 -0.12 0.0094 -0.0128 Value02=-0.50 -0.07 0.0057 -0.0141 Value03=0.00 -0.01 0.0057 -0.0145 Value04=1.00 0.09 0.0056 -0.0152 Value05=2.00 0.21 0.0058 -0.0186 Value06=3.00 0.33 0.0061 -0.0223 Value07=4.00 0.44 0.0069 -0.0242 Value08=4.50 0.50 0.0076 -0.0247 Value09=5.00 0.55 0.0088 -0.0251 Value10=5.50 0.60 0.0103 -0.0248 Value11=6.00 0.65 0.0118 -0.0244 Value12=7.00 0.75 0.0134 -0.0239 Value13=8.00 0.85 0.0146 -0.0233 [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 -0.17 0.0088 -0.0148 Value02=-1.00 -0.11 0.0086 -0.0152 Value03=-0.50 -0.06 0.0048 -0.0157 Value04=0.00 -0.00 0.0048 -0.0161 Value05=1.00 0.10 0.0047 -0.0173 Value06=2.00 0.23 0.0049 -0.0215 Value07=3.00 0.33 0.0053 -0.0227 Value08=4.00 0.44 0.0061 -0.0240 Value09=4.50 0.50 0.0067 -0.0247 Value10=5.00 0.55 0.0078 -0.0253 Value11=5.50 0.60 0.0093 -0.0256 Value12=6.00 0.65 0.0108 -0.0252 Value13=7.00 0.75 0.0123 -0.0248 Value14=8.00 0.85 0.0135 -0.0244 [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 -0.22 0.0082 -0.0146 Value02=-1.50 -0.17 0.0079 -0.0152 Value03=-1.00 -0.11 0.0077 -0.0159 Value04=-0.50 -0.06 0.0040 -0.0165 Value05=0.00 0.00 0.0039 -0.0172 Value06=1.00 0.11 0.0041 -0.0186 Value07=2.00 0.22 0.0043 -0.0201 Value08=3.00 0.33 0.0049 -0.0221 Value09=4.00 0.44 0.0058 -0.0235 Value10=4.50 0.50 0.0064 -0.0243 Value11=5.00 0.55 0.0071 -0.0251 Value12=5.50 0.60 0.0082 -0.0258 Value13=6.00 0.66 0.0096 -0.0260 Value14=7.00 0.76 0.0111 -0.0260 Value15=8.00 0.86 0.0122 -0.0258 [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 0.0077 -0.0135 Value02=-2.00 -0.22 0.0072 -0.0146 Value03=-1.50 -0.17 0.0070 -0.0152 Value04=-1.00 -0.11 0.0069 -0.0159 Value05=-0.50 -0.06 0.0041 -0.0165 Value06=0.00 0.00 0.0038 -0.0172 Value07=1.00 0.11 0.0039 -0.0186 Value08=2.00 0.22 0.0043 -0.0201 Value09=3.00 0.33 0.0050 -0.0216 Value10=4.00 0.44 0.0057 -0.0233 Value11=4.50 0.50 0.0061 -0.0241 Value12=5.00 0.55 0.0066 -0.0250 Value13=5.50 0.61 0.0072 -0.0259 Value14=6.00 0.66 0.0083 -0.0267 Value15=7.00 0.77 0.0097 -0.0276 Value16=8.00 0.87 0.0106 -0.0278