; This is a polar exchange file ; Comments start with a ';' in column 1 [Airfoil] ; obsolete: Airfoilname=MH 27 ; new: Description1=MH 27 NumberSets=1 [Set1] Origin=Eppler PROFIL (calculation) Description1=Copyright 1996 Martin Hepperle Description2=Created Mon May 13 13:01:32 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=14 ;---- Alpha Cl Cd Cm Value01=-1.50 -0.21 0.0131 -0.0183 Value02=-1.00 -0.13 0.0092 -0.0259 Value03=-0.50 -0.08 0.0092 -0.0260 Value04=0.00 -0.03 0.0091 -0.0261 Value05=1.00 0.06 0.0091 -0.0265 Value06=2.00 0.16 0.0092 -0.0270 Value07=3.00 0.26 0.0093 -0.0273 Value08=4.00 0.38 0.0098 -0.0329 Value09=4.50 0.44 0.0100 -0.0350 Value10=5.00 0.50 0.0104 -0.0377 Value11=5.50 0.56 0.0111 -0.0403 Value12=6.00 0.62 0.0120 -0.0418 Value13=7.00 0.72 0.0153 -0.0431 Value14=8.00 0.81 0.0188 -0.0431 [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=14 ;---- Alpha Cl Cd Cm Value01=-1.50 -0.20 0.0110 -0.0198 Value02=-1.00 -0.13 0.0067 -0.0255 Value03=-0.50 -0.08 0.0066 -0.0258 Value04=0.00 -0.03 0.0066 -0.0262 Value05=1.00 0.07 0.0066 -0.0269 Value06=2.00 0.17 0.0067 -0.0278 Value07=3.00 0.27 0.0068 -0.0286 Value08=4.00 0.40 0.0072 -0.0358 Value09=4.50 0.46 0.0074 -0.0380 Value10=5.00 0.52 0.0078 -0.0400 Value11=5.50 0.57 0.0084 -0.0417 Value12=6.00 0.62 0.0094 -0.0427 Value13=7.00 0.72 0.0126 -0.0437 Value14=8.00 0.82 0.0161 -0.0440 [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=15 ;---- Alpha Cl Cd Cm Value01=-2.00 -0.25 0.0103 -0.0210 Value02=-1.50 -0.19 0.0100 -0.0217 Value03=-1.00 -0.13 0.0056 -0.0259 Value04=-0.50 -0.08 0.0055 -0.0265 Value05=0.00 -0.02 0.0055 -0.0272 Value06=1.00 0.08 0.0055 -0.0284 Value07=2.00 0.18 0.0056 -0.0298 Value08=3.00 0.30 0.0058 -0.0349 Value09=4.00 0.41 0.0062 -0.0385 Value10=4.50 0.47 0.0066 -0.0401 Value11=5.00 0.52 0.0071 -0.0413 Value12=5.50 0.57 0.0077 -0.0422 Value13=6.00 0.63 0.0085 -0.0429 Value14=7.00 0.72 0.0113 -0.0438 Value15=8.00 0.82 0.0148 -0.0443 [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=16 ;---- Alpha Cl Cd Cm Value01=-3.00 -0.33 0.0098 -0.0230 Value02=-2.00 -0.23 0.0091 -0.0243 Value03=-1.50 -0.18 0.0089 -0.0250 Value04=-1.00 -0.12 0.0045 -0.0273 Value05=-0.50 -0.07 0.0045 -0.0281 Value06=0.00 -0.02 0.0044 -0.0288 Value07=1.00 0.09 0.0044 -0.0303 Value08=2.00 0.20 0.0046 -0.0341 Value09=3.00 0.31 0.0049 -0.0371 Value10=4.00 0.42 0.0057 -0.0394 Value11=4.50 0.47 0.0061 -0.0403 Value12=5.00 0.52 0.0067 -0.0412 Value13=5.50 0.57 0.0074 -0.0419 Value14=6.00 0.62 0.0081 -0.0426 Value15=7.00 0.73 0.0100 -0.0438 Value16=8.00 0.82 0.0133 -0.0444 [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 0.0085 -0.0252 Value02=-2.00 -0.22 0.0079 -0.0267 Value03=-1.50 -0.17 0.0076 -0.0275 Value04=-1.00 -0.12 0.0045 -0.0277 Value05=-0.50 -0.06 0.0039 -0.0285 Value06=0.00 -0.01 0.0035 -0.0296 Value07=1.00 0.10 0.0037 -0.0327 Value08=2.00 0.21 0.0041 -0.0347 Value09=3.00 0.31 0.0048 -0.0365 Value10=4.00 0.42 0.0056 -0.0383 Value11=4.50 0.47 0.0061 -0.0393 Value12=5.00 0.52 0.0066 -0.0403 Value13=5.50 0.57 0.0072 -0.0412 Value14=6.00 0.62 0.0079 -0.0422 Value15=7.00 0.73 0.0093 -0.0438 Value16=8.00 0.83 0.0116 -0.0449