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SUAVE
2.5.2
An Aerospace Vehicle Environment for Designing Future Aircraft
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SUAVE
2.5.2
An Aerospace Vehicle Environment for Designing Future Aircraft
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| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cl_beta.cl_beta | ( | geometry, | |
| cl_p | |||
| ) |
cl_beta.py
Created: Aug 2016, A. van Korlaar Modified: Aug 2016, L. Kulik
THis calculates the derivative of roll rate with respect to sideslip (dihedral effect) Assumptions: None: Source: STABILITY, USAF. "Control Datcom." Air Force Flight Dynamics Laboratory, Wright-Patterson Air Force Base, Ohio (1972) Inputs: dihedral [radians] taper [dimensionless] Outputs: cl_beta [dimensionless] Properties Used: N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cl_p.cl_p | ( | cl_alpha, | |
| geometry | |||
| ) |
cl_p.py
Created: Aug 2016, A. van Korlaar Modified: Aug 2016, L. Kulik
This calculates the derivative of rolling moment with respect to roll rate Assumptions: None Source: STABILITY, USAF. "Control Datcom." Air Force Flight Dynamics Laboratory, Wright-Patterson Air Force Base, Ohio (1972) Inputs: taper [dimensionless] cl_alpha [dimensionless] Outputs: cl_p [dimensionless] Properties Used: N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cl_r.cl_r | ( | cLw | ) |
cl_r.py
Created: Jun 2014, A. Wendorff Modified: Jan 2016, E. Botero
This calculates the rolling moment coefficient with respect to
perturbational angular rate around the z-body-axis
Assumptions:
None
Source:
J.H. Blakelock, "Automatic Control of Aircraft and Missiles"
Wiley & Sons, Inc. New York, 1991, (pg 23
Inputs:
clw [dimensionless]
Outputs:
cl_r [dimensionless]
Properties Used:
N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cm_alphadot.cm_alphadot | ( | cm_i, | |
| ep_alpha, | |||
| l_t, | |||
| mac | |||
| ) |
cm_alphadot.py
Created: Jun 2014, A. Wendorff Modified: Jan 2016, E. Botero
This calculates the pitching moment coefficient with respect to the
rate of change of the alpha of attack of the aircraft
Assumptions:
None
Source:
J.H. Blakelock, "Automatic Control of Aircraft and Missiles"
Wiley & Sons, Inc. New York, 1991, (pg 23)
Inputs:
cm_i [dimensionless]
ep_alpha [dimensionless]
l_t [meters]
mac [meters]
Outputs:
cm_alphadot [dimensionless]
Properties Used:
N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cm_q.cm_q | ( | cm_i, | |
| l_t, | |||
| mac | |||
| ) |
cm_q.py
Created: Jun 2014, A. Wendorff Modified: Jan 2016, E. Botero
This calculates the damping in pitch coefficient Assumptions: None Source: J.H. Blakelock, "Automatic Control of Aircraft and Missiles" Wiley & Sons, Inc. New York, 1991, (pg 23) Inputs: cm_i [dimensionless] l_t [meters] mac [meters] Outputs: cm_q [dimensionless] Properties Used: N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cn_p.cn_p | ( | cLw, | |
| depdalpha | |||
| ) |
cn_p.py
Created: Jun 2014, A. Wendorff Modified: Jan 2016, E. Botero
This calculats the yawing moment coefficient with respect
to perturbational angular rate around the x-body-axis
Assumptions:
None
Source:
J.H. Blakelock, "Automatic Control of Aircraft and Missiles"
Wiley & Sons, Inc. New York, 1991, (pg 23)
Inputs:
clw [dimensionless]
dep_alpha [dimensionless]
Outputs:
cn_p [dimensionless]
Properties Used:
N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cn_r.cn_r | ( | cDw, | |
| Sv, | |||
| Sref, | |||
| l_v, | |||
| span, | |||
| eta_v, | |||
| cLv_alpha | |||
| ) |
cn_r.py
Created: Jun 2014, A. Wendorff Modified: Jan 2016, E. Botero
This calculats the yawing moment coefficient with respect to
perturbational angular rate around the z-body-axis
Assumptions:
None
Source:
J.H. Blakelock, "Automatic Control of Aircraft and Missiles"
Wiley & Sons, Inc. New York, 1991, (pg 23)
Inputs:
eta_v [dimensionless]
cDw [dimensionless]
l_v [meters]
span [meters]
Sref [meters**2]
Sv [meters**2]
Outputs:
cn_r [dimensionless]
Properties Used:
N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cx_alpha.cx_alpha | ( | cL, | |
| cL_alpha | |||
| ) |
cx_alpha.py
Created: Jun 2014, A. Wendorff Modified: Jan 2016, E. Botero
This calculates the coefficient of force in the x direction
with respect to the change in angle of attack of the aircraft
Assumptions:
None
Source:
J.H. Blakelock, "Automatic Control of Aircraft and Missiles"
Wiley & Sons, Inc. New York, 1991, (pg 23)
Inputs:
cL [dimensionless]
cL_alpha [dimensionless]
Outputs:
cx_alpha [dimensionless]
Properties Used:
N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cx_u.cx_u | ( | cD | ) |
cx_u.py
Created: Jun 2014, A. Wendorff Modified: Jan 2016, E. Botero
This calculates the coefficient of force in the x direction with respect to the change in forward velocity of the aircraft Assumptions: None Source: J.H. Blakelock, "Automatic Control of Aircraft and Missiles" Wiley & Sons, Inc. New York, 1991, (pg 23) Inputs: cD [dimensionless] Outputs: cx_u [dimensionless] Properties Used: N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cy_phi.cy_phi | ( | CL | ) |
cy_phi.py
Created: Jun 2014, A. Wendorff Modified: Jan 2016, E. Botero
This calculates the force coefficient in the y direction with respect to the roll angle of the aircraft Assumptions: None Source: J.H. Blakelock, "Automatic Control of Aircraft and Missiles" Wiley & Sons, Inc. New York, 1991, (pg 23) Inputs: CL [dimensionless] Outputs: cy_phi [dimensionless] Properties Used: N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cz_alphadot.cz_alphadot | ( | cm_i, | |
| ep_alpha | |||
| ) |
cz_alphadot.py
Created: Jun 2014, A. Wendorff Modified: Jan 2016, E. Botero
This calculates the coefficient of force in the z direction with respect to the rate of change of the alpha of attack of the aircraft Assumptions: None Source: J.H. Blakelock, "Automatic Control of Aircraft and Missiles" Wiley & Sons, Inc. New York, 1991, (pg 23) Inputs: cm_i [dimensionless] ep_alpha [dimensionless] Outputs: cz_alphadot [dimensionless] Properties Used: N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cz_q.cz_q | ( | cm_i | ) |
cz_q.py
Created: Jun 2014, A. Wendorff Modified: Jan 2016, E. Botero
This calculates the coefficient of force in the z direction with respect to the rate of change of the alpha of attack of the aircraft Assumptions: None Source: J.H. Blakelock, "Automatic Control of Aircraft and Missiles" Wiley & Sons, Inc. New York, 1991, (pg 23) Inputs: cm_i [dimensionless] Outputs: cz_q [dimensionless] Properties Used: N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.cz_u.cz_u | ( | cL, | |
| U, | |||
cL_u = 0 |
|||
| ) |
cz_u.py
Created: Jun 2014, A. Wendorff Modified: Jan 2016, E. Botero
This calculates the coefficient of force in the z direction with respect to the change in the forward velocity Assumptions: None Source: J.H. Blakelock, "Automatic Control of Aircraft and Missiles" Wiley & Sons, Inc. New York, 1991, (pg 23) Inputs: cL [dimensionless] U [meters/second] cL_u Outputs: cz_u [dimensionless] Properties Used: N/A
| def SUAVE.Methods.Flight_Dynamics.Dynamic_Stability.Full_Linearized_Equations.Supporting_Functions.ep_alpha.ep_alpha | ( | cL_w_alpha, | |
| Sref, | |||
| span | |||
| ) |
Calculates the change in the downwash with change in
angle of attack
Assumptions:
None
Source:
J.H. Blakelock, "Automatic Control of Aircraft and Missiles"
Wiley & Sons, Inc. New York, 1991, (pg 34)
Inputs:
span [meters]
Sref [square meters]
cL_w_alpha [unitless]
Outputs:
ep_alpha [Unitless]
Properties Used:
N/A
1.8.15