#*************************************** #AVL dataset for Meridian wing/tail #*************************************** MERIDIAN #Mach 0.181 #IYsym IZsym Zsym 0 0 0.0 #Sref Cref Bref 6.466981 0.804164 8.04164 # # #AVL Axes: # +X downstream # +Y out the right wing # +Z up # # #Xref, Yref, Zref is the c.g. location. #c.g. is 0.157m in front of the wing trailing edge #root chord is 0.254 #X value (from wing LE) is 0.242-0.157 = 0.085 #Z c.g. is 0.09m #Xref Yref Zref #0.29845 0.0 0.0 0.16080 0.0 0.0 # # #*********************************** SURFACE RWing #Nchordwise Cspace Nspanwise Sspace 10 1.0 15 -2.0 # #=================Root section SECTION #Xle Yle Zle Chord AngleOfIncidence 0.0 0.0 0.0 0.804164 0.0 15 -2.0 # AFILE clarky.dat # #Set dcl/da = 2 pi CLaf, i.e. CLaf = CLalpha/(2*pi) CLAF 0.9949 # #Set parabolic drag polar #CL1 CD1 CL2 CD2 CL3 CD3 | CD(CL) function parameters CDCL 0.1759 0.00637 0.4051 0.00615 1.4416 0.01392 # # =================Define Section where Flap starts SECTION #Xle Yle Zle Chord AngleOfIncidence 0.0 0.402082 0.0 0.804164 0.0 15 -2.0 # CONTROL #label gain xfrac vx vy vz sgn Rflap 1.0 0.75 0. 0. 0. 1. # AFILE clarky.dat # #Set dcl/da = 2 pi CLaf, i.e. CLaf = CLalpha/(2*pi) CLAF 0.9949 # #Set parabolic drag polar #CL1 CD1 CL2 CD2 CL3 CD3 | CD(CL) function parameters CDCL 0.1759 0.00637 0.4051 0.00615 1.4416 0.01392 # #=================Define End of Flap Section SECTION #Xle Yle Zle Chord AngleOfIncidence 0. 2.088134 0. 0.804164 0. 15 -2.0 # CONTROL #label gain xfrac vx vy vz sgn Rflap 1.0 0.75 0. 0. 0. 1. # AFILE clarky.dat # #Set dcl/da = 2 pi CLaf, i.e. CLaf = CLalpha/(2*pi) CLAF 0.9949 # #Set parabolic drag polar #CL1 CD1 CL2 CD2 CL3 CD3 | CD(CL) function parameters CDCL 0.1759 0.00637 0.4051 0.00615 1.4416 0.01392 # #=================Define Start of Aileron Section SECTION #Xle Yle Zle Chord AngleOfIncidence 0. 2.412492 0. 0.804164 0. 15 -2.0 # CONTROL #label gain xfrac vx vy vz sgn Raileron 1.0 0.75 0. 0. 0. -1. # AFILE clarky.dat # #Set dcl/da = 2 pi CLaf, i.e. CLaf = CLalpha/(2*pi) CLAF 0.9949 # #Set parabolic drag polar #CL1 CD1 CL2 CD2 CL3 CD3 | CD(CL) function parameters CDCL 0.1759 0.00637 0.4051 0.00615 1.4416 0.01392 # #=================Define wingtip section SECTION #Xle Yle Zle Chord AngleOfIncidence 0.0000 4.02082 0.0000 0.804164 0. 15 -2.0 # CONTROL #label gain xfrac vx vy vz sgn Raileron 1.0 0.75 0. 0. 0. -1. # AFILE clarky.dat # #Set dcl/da = 2 pi CLaf, i.e. CLaf = CLalpha/(2*pi) CLAF 0.9949 # #Set parabolic drag polar #CL1 CD1 CL2 CD2 CL3 CD3 | CD(CL) function parameters CDCL 0.1759 0.00637 0.4051 0.00615 1.4416 0.01392 # #*********************************** SURFACE LWing #Nchordwise Ccpace Nspanwise Sspace 10 1.0 15 2.0 # # #=================Define wingtip section SECTION #Xle Yle Zle Chord AngleOfIncidence 0.00 -4.02082 0 0.804164 0. 15 2.0 # CONTROL #label gain xfrac vx vy vz sgn Laileron 1.0 0.75 0. 0. 0. -1. # AFILE clarky.dat # #Set dcl/da = 2 pi CLaf, i.e. CLaf = CLalpha/(2*pi) CLAF 0.9949 # #Set parabolic drag polar #CL1 CD1 CL2 CD2 CL3 CD3 | CD(CL) function parameters CDCL 0.1759 0.00637 0.4051 0.00615 1.4416 0.01392 # #=================Define Start of Aileron SECTION #Xle Yle Zle Chord AngleOfIncidence 0. -2.412492 0. 0.804164 0. 15 2.0 # CONTROL #label gain xfrac vx vy vz sgn Laileron 1.0 0.75 0. 0. 0. -1. # AFILE clarky.dat # #Set dcl/da = 2 pi CLaf, i.e. CLaf = CLalpha/(2*pi) CLAF 0.9949 # #Set parabolic drag polar #CL1 CD1 CL2 CD2 CL3 CD3 | CD(CL) function parameters CDCL 0.1759 0.00637 0.4051 0.00615 1.4416 0.01392 # #===================Define End of Flap SECTION #Xle Yle Zle Chord AngleOfIncidence 0. -2.088134 0. 0.804164 0. 15 2.0 # CONTROL #label gain xfrac vx vy vz sgn Lflap 1.0 0.75 0. 0. 0. 1. # AFILE clarky.dat # #Set dcl/da = 2 pi CLaf, i.e. CLaf = CLalpha/(2*pi) CLAF 0.9949 # #Set parabolic drag polar #CL1 CD1 CL2 CD2 CL3 CD3 | CD(CL) function parameters CDCL 0.1759 0.00637 0.4051 0.00615 1.4416 0.01392 # #=================Define Start of Flap SECTION #Xle Yle Zle Chord AngleOfIncidence 0.0 -0.402082 0.0 0.804164 0.0 15 2.0 # CONTROL #label gain xfrac vx vy vz sgn Lflap 1.0 0.75 0. 0. 0. 1. # AFILE clarky.dat # #Set dcl/da = 2 pi CLaf, i.e. CLaf = CLalpha/(2*pi) CLAF 0.9949 # #Set parabolic drag polar #CL1 CD1 CL2 CD2 CL3 CD3 | CD(CL) function parameters CDCL 0.1759 0.00637 0.4051 0.00615 1.4416 0.01392 # #=================Root section SECTION #Xle Yle Zle Chord AngleOfIncidence 0. 0. 0. 0.804164 0. 15 2.0 # AFILE clarky.dat # #Set dcl/da = 2 pi CLaf, i.e. CLaf = CLalpha/(2*pi) CLAF 0.9949 # #Set parabolic drag polar #CL1 CD1 CL2 CD2 CL3 CD3 | CD(CL) function parameters CDCL 0.1759 0.00637 0.4051 0.00615 1.4416 0.01392 # # #*********************************** SURFACE RTail #Nchordwise Cspace Nspanwise Sspace 8 1.0 8 1.0 TRANSLATE 3.175 0. 0. # # # #=================Tail Root Section SECTION #Xle Yle Zle Chord AngleOfIncidence 0. 0. 0 0.686816 0 8 1.0 # NACA 0009 # CONTROL #label gain xfrac vx vy vz sgn Rveetail 1 0.01 0. 0. 0. 1. # # # #=================Tail tip section SECTION #Xle Yle Zle Chord AngleOfIncidence 0.531114 0.9017 1.074674 0.343408 0 8 1.0 # NACA 0009 # # CONTROL #label gain xfrac vx vy vz sgn Rveetail 1 0.01 0. 0. 0. 1. # # #*********************************** SURFACE LTail #Nchordwise Cspace Nspanwise Sspace 8 1.0 8 1.0 TRANSLATE 3.175 0. 0. # #=================Tail tip section SECTION #Xle Yle Zle Chord AngleOfIncidence 0.531114 -0.9017 1.074674 0.343408 0 8 1.0 # NACA 0009 # # CONTROL #label gain xfrac vx vy vz sgn Lveetail 1 0.01 0. 0. 0. 1. # # #=================Tail Root section SECTION #Xle Yle Zle Chord AngleOfIncidence 0. 0. 0. 0.686816 0 8 1.0 # NACA 0009 # # CONTROL #label gain xfrac vx vy vz sgn Lveetail 1 0.01 0. 0. 0. 1.