Optional outputs that echo the inputs. These are parsed from the resulting output and can be used as a sanity check.

• Alpha = Angle of attack.
• Beta = Sideslip angle.
• Mach = Mach number.
• pb/2V = Non-dimensional roll rate.
• qc/2V = Non-dimensional pitch rate.
• rb/2V = Non-dimensional yaw rate.
• p'b/2V = Non-dimensional roll acceleration.
• r'b/2V = Non-dimensional yaw acceleration.

Forces and moments:

• CXtot = X-component of total force in body axis
• CYtot = Y-component of total force in body axis
• CZtot = Z-component of total force in body axis
• Cltot = X-component of moment in body axis
• Cmtot = Y-component of moment in body axis
• Cntot = Z-component of moment in body axis
• Cl'tot = x-component of moment in stability axis
• Cn'tot = z-component of moment in stability axis
• CLtot = total lift in stability axis
• CDtot = total drag in stability axis
• CDvis = viscous drag component
• CLff = trefftz plane lift force
• CYff = trefftz plane side force
• CDind = induced drag force
• CDff = trefftz plane drag force
• e = Oswald Efficiency

Stability-axis derivatives - Alpha:

• CLa = z' force, CL, with respect to alpha.
• CYa = y force, CY, with respect to alpha.
• Cl'a = x' moment, Cl', with respect to alpha.
• Cma = y moment, Cm, with respect to alpha.
• Cn'a = z' moment, Cn', with respect to alpha.

Stability-axis derivatives - Beta:

• CLb = z' force, CL, with respect to beta.
• CYb = y force, CY, with respect to beta.
• Cl'b = x' moment, Cl', with respect to beta.
• Cmb = y moment, Cm, with respect to beta.
• Cn'b = z' moment, Cn', with respect to beta.

Stability-axis derivatives - Roll rate, p':

• CLp' = z' force, CL, with respect to roll rate, p'.
• CYp' = y force, CY, with respect to roll rate, p'.
• Cl'p' = x' moment, Cl', with respect to roll rate, p'.
• Cmp' = y moment, Cm, with respect to roll rate, p'.
• Cn'p' = z' moment, Cn', with respect to roll rate, p'.

Stability-axis derivatives - Pitch rate, q':

• CLq' = z' force, CL, with respect to pitch rate, q'.
• CYq' = y force, CY, with respect to pitch rate, q'.
• Cl'q' = x' moment, Cl', with respect to pitch rate, q'.
• Cmq' = y moment, Cm, with respect to pitch rate, q'.
• Cn'q' = z' moment, Cn', with respect to pitch rate, q'.

Stability-axis derivatives - Yaw rate, r':

• CLr' = z' force, CL, with respect to yaw rate, r'.
• CYr' = y force, CY, with respect to yaw rate, r'.
• Cl'r' = x' moment, Cl', with respect to yaw rate, r'.
• Cmr' = y moment, Cm, with respect to yaw rate, r'.
• Cn'r' = z' moment, Cn', with respect to yaw rate, r'.

Body-axis derivatives - Axial velocity, u:

• CXu = x force, CX, with respect to axial velocity, u.
• CYu = y force, CY, with respect to axial velocity, u.
• CZu = z force, CZ, with respect to axial velocity, u.
• Clu = x moment, Cl, with respect to axial velocity, u.
• Cmu = y moment, Cm, with respect to axial velocity, u.
• Cnu = z moment, Cn, with respect to axial velocity, u.

Body-axis derivatives - Sideslip velocity, v:

• CXv = x force, CX, with respect to sideslip velocity, v.
• CYv = y force, CY, with respect to sideslip velocity, v.
• CZv = z force, CZ, with respect to sideslip velocity, v.
• Clv = x moment, Cl, with respect to sideslip velocity, v.
• Cmv = y moment, Cm, with respect to sideslip velocity, v.
• Cnv = z moment, Cn, with respect to sideslip velocity, v.

Body-axis derivatives - Normal velocity, w:

• CXw = x force, CX, with respect to normal velocity, w.
• CYw = y force, CY, with respect to normal velocity, w.
• CZw = z force, CZ, with respect to normal velocity, w.
• Clw = x moment, Cl, with respect to normal velocity, w.
• Cmw = y moment, Cm, with respect to normal velocity, w.
• Cnw = z moment, Cn, with respect to normal velocity, w.

Body-axis derivatives - Roll rate, p:

• CXp = x force, CX, with respect to roll rate, p.
• CYp = y force, CY, with respect to roll rate, p.
• CZp = z force, CZ, with respect to roll rate, p.
• Clp = x moment, Cl, with respect to roll rate, p.
• Cmp = y moment, Cm, with respect to roll rate, p.
• Cnp = z moment, Cn, with respect to roll rate, p.

Body-axis derivatives - Pitch rate, q:

• CXq = x force, CX, with respect to pitch rate, q.
• CYq = y force, CY, with respect to pitch rate, q.
• CZq = z force, CZ, with respect to pitch rate, q.
• Clq = x moment, Cl, with respect to pitch rate, q.
• Cmq = y moment, Cm, with respect to pitch rate, q.
• Cnq = z moment, Cn, with respect to pitch rate, q.

Body-axis derivatives - Yaw rate, r:

• CXr = x force, CX, with respect to yaw rate, r.
• CYr = y force, CY, with respect to yaw rate, r.
• CZr = z force, CZ, with respect to yaw rate, r.
• Clr = x moment, Cl, with respect to yaw rate, r.
• Cmr = y moment, Cm, with respect to yaw rate, r.
• Cnr = z moment, Cn, with respect to yaw rate, r.

Geometric output:

• Xnp = Neutral Point
• Xcg = x CG location
• Ycg = y CG location
• Zcg = z CG location
  Note: CG location calculation requires mass properties

Controls:

• ControlStability = a (or an array of) tuple(s) with a structure of ("Control Surface Name", "JSON Dictionary") for all control surfaces in the stability axis frame. The JSON dictionary has the form = {"CLtot":value,"CYtot":value,"Cl'tot":value,"Cmtot":value,"Cn'tot":value}
• ControlBody = a (or an array of) tuple(s) with a structure of ("Control Surface Name", "JSON Dictionary") for all control surfaces in the body axis frame. The JSON dictionary has the form = {"CXtot":value,"CYtot":value,"CZtot":value,"Cltot":value,"Cmtot":value,"Cntot":value}
• ControlDeflection = a (or an array of) tuple(s) with a structure of ("Control Surface Name", "Deflection")
• HingeMoment = a (or an array of) tuple(s) with a structure of ("Control Surface Name", "HingeMoment")
• StripForces = a (or an array of) tuple(s) with a structure of ("Surface Name", "JSON Dictionary") for all surfaces. The JSON dictionary has the form = {"cl":[value0,value1,value2],"cd":[value0,value1,value2]...}
• EigenValues = a (or an array of) tuple(s) with a structure of ("case #", "Array of eigen values"). The array of eigen values is of the form = [[real0,imaginary0],[real0,imaginary0],...]