; This is a polar exchange file ; Comments start with a ';' in column 1 [Airfoil] ; obsolete: Airfoilname=MH 24 ; new: Description1=MH 24 NumberSets=1 [Set1] Origin=Eppler PROFIL (calculation) Description1=Copyright 1996 Martin Hepperle Description2=Created Mon May 13 12:32:07 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 -0.14 0.0114 -0.0194 Value02=-0.50 -0.06 0.0081 -0.0249 Value03=0.00 -0.02 0.0081 -0.0244 Value04=1.00 0.08 0.0081 -0.0237 Value05=2.00 0.18 0.0081 -0.0232 Value06=3.00 0.30 0.0085 -0.0274 Value07=4.00 0.43 0.0091 -0.0316 Value08=4.50 0.48 0.0096 -0.0333 Value09=5.00 0.54 0.0103 -0.0344 Value10=5.50 0.59 0.0116 -0.0348 Value11=6.00 0.64 0.0133 -0.0346 Value12=7.00 0.74 0.0159 -0.0339 Value13=8.00 0.84 0.0173 -0.0338 [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 -0.13 0.0096 -0.0212 Value02=-0.50 -0.06 0.0059 -0.0250 Value03=0.00 -0.01 0.0059 -0.0249 Value04=1.00 0.09 0.0059 -0.0246 Value05=2.00 0.19 0.0059 -0.0245 Value06=3.00 0.32 0.0062 -0.0306 Value07=4.00 0.44 0.0068 -0.0343 Value08=4.50 0.49 0.0073 -0.0355 Value09=5.00 0.55 0.0081 -0.0361 Value10=5.50 0.60 0.0093 -0.0363 Value11=6.00 0.65 0.0110 -0.0361 Value12=7.00 0.75 0.0136 -0.0355 Value13=8.00 0.85 0.0149 -0.0354 [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 0.0089 -0.0234 Value02=-1.00 -0.12 0.0086 -0.0238 Value03=-0.50 -0.06 0.0050 -0.0261 Value04=0.00 -0.00 0.0049 -0.0263 Value05=1.00 0.10 0.0049 -0.0267 Value06=2.00 0.22 0.0051 -0.0307 Value07=3.00 0.33 0.0054 -0.0330 Value08=4.00 0.44 0.0061 -0.0347 Value09=4.50 0.49 0.0066 -0.0356 Value10=5.00 0.55 0.0072 -0.0364 Value11=5.50 0.60 0.0083 -0.0370 Value12=6.00 0.65 0.0099 -0.0369 Value13=7.00 0.75 0.0125 -0.0364 Value14=8.00 0.85 0.0137 -0.0365 [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 -0.0243 Value02=-1.50 -0.17 0.0080 -0.0250 Value03=-1.00 -0.11 0.0078 -0.0258 Value04=-0.50 -0.06 0.0040 -0.0266 Value05=0.00 -0.00 0.0040 -0.0273 Value06=1.00 0.11 0.0040 -0.0291 Value07=2.00 0.22 0.0043 -0.0310 Value08=3.00 0.33 0.0049 -0.0328 Value09=4.00 0.44 0.0057 -0.0347 Value10=4.50 0.49 0.0063 -0.0356 Value11=5.00 0.55 0.0069 -0.0365 Value12=5.50 0.60 0.0076 -0.0374 Value13=6.00 0.66 0.0087 -0.0380 Value14=7.00 0.76 0.0113 -0.0378 Value15=8.00 0.86 0.0124 -0.0380 [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 -0.0229 Value02=-2.00 -0.22 0.0073 -0.0243 Value03=-1.50 -0.17 0.0071 -0.0250 Value04=-1.00 -0.11 0.0069 -0.0258 Value05=-0.50 -0.06 0.0039 -0.0266 Value06=0.00 0.00 0.0036 -0.0274 Value07=1.00 0.11 0.0037 -0.0292 Value08=2.00 0.22 0.0042 -0.0310 Value09=3.00 0.33 0.0048 -0.0328 Value10=4.00 0.44 0.0056 -0.0348 Value11=4.50 0.49 0.0061 -0.0357 Value12=5.00 0.55 0.0067 -0.0367 Value13=5.50 0.60 0.0072 -0.0376 Value14=6.00 0.66 0.0079 -0.0385 Value15=7.00 0.76 0.0100 -0.0395 Value16=8.00 0.87 0.0109 -0.0400