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Address issue #620 #623

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merged 3 commits into from
Nov 6, 2022
Merged

Address issue #620 #623

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89047af
Update cm_q.py
danielenriquez59 Nov 4, 2022
dfdd415
Update Fidelity_Zero.py
danielenriquez59 Nov 4, 2022
d0cdc76
Merge branch 'develop' into develop
planes Nov 6, 2022
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3 changes: 2 additions & 1 deletion trunk/SUAVE/Analyses/Stability/Fidelity_Zero.py
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Expand Up @@ -185,7 +185,8 @@ def __call__(self,conditions):

# Derivative of pitching moment with respect to pitch rate
l_t = geometry.wings['horizontal_stabilizer'].origin[0][0] + geometry.wings['horizontal_stabilizer'].aerodynamic_center[0] - geometry.wings['main_wing'].origin[0][0] - geometry.wings['main_wing'].aerodynamic_center[0] #Need to check this is the length of the horizontal tail moment arm
stability.static.Cm_q = Supporting_Functions.cm_q(conditions.lift_curve_slope, l_t,mac) # Need to check Cm_i versus Cm_alpha
vht = geometry.wings['horizontal_stabilizer'].areas.reference * l_t / (geometry.reference_area*geometry.wings['main_wing'].chords.mean_aerodynamic)
stability.static.Cm_q = Supporting_Functions.cm_q(conditions.lift_curve_slope, vht, l_t,mac) # Need to check Cm_i versus Cm_alpha

# Derivative of pitching rate with respect to d(alpha)/d(t)
stability.static.Cm_alpha_dot = Supporting_Functions.cm_alphadot(stability.static.Cm_alpha, geometry.wings['horizontal_stabilizer'].ep_alpha, l_t, mac) # Need to check Cm_i versus Cm_alpha
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9 changes: 5 additions & 4 deletions .../Flight_Dynamics/Dynamic_Stability/Full_Linearized_Equations/Supporting_Functions/cm_q.py
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Expand Up @@ -3,13 +3,14 @@
#
# Created: Jun 2014, A. Wendorff
# Modified: Jan 2016, E. Botero
# Modified: Nov 2022, D. Enriquez

# ----------------------------------------------------------------------
# Method
# ----------------------------------------------------------------------

## @ingroup Methods-Flight_Dynamics-Dynamic_Stability-Full_Linearized_Equations-Supporting_Functions
def cm_q(cm_i, l_t, mac):
def cm_q(cla, vht, l_t, mac):
""" This calculates the damping in pitch coefficient

Assumptions:
Expand All @@ -30,6 +31,6 @@ def cm_q(cm_i, l_t, mac):
Properties Used:
N/A
"""
cm_q = 2. * 1.1 * cm_i * l_t / mac

return cm_q
cm_q = -2. * l_t / mac * vht * cla
cm_q = cm_q * 1.1 # factor to account for fuselage contribution
return cm_q