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
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}
- 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],...]