Source code for RCAIDE.Library.Methods.Geometry.Planform.vertical_tail_planform_raymer
# vertical_tail_planform_raymer.py
#
# Created: ### ####, M. Vegh
# Modified: Jan 2016, E. Botero
# ----------------------------------------------------------------------
# Imports
# ----------------------------------------------------------------------
from RCAIDE.Library.Methods.Geometry.Planform import wing_planform
# ----------------------------------------------------------------------
# Methods
# ----------------------------------------------------------------------
[docs]
def vertical_tail_planform_raymer(vertical_stabilizer, wing, l_vt,c_vt):
"""Adjusts reference area before calling generic wing planform function to compute wing planform values.
Assumptions:
None
Source:
Raymer
Inputs:
vertical_stabilizer [RCAIDE data structure]
wing [RCAIDE data structure] (should be the main wing)
l_vt [m] length from wing mean aerodynamic chord (MAC) to horizontal stabilizer MAC
c_vt [-] horizontal tail coefficient (Raymer specific) .02 = Sailplane, .04 = homebuilt,
.04 = GA single engine, .07 = GA twin engine, .04 = agricultural,
.08 = twin turboprop, .06 = flying boat, .06 = jet trainer, .07 = jet fighter
.08 = military cargo/bomber, .09 = jet transport
Outputs:
vertical_stabilier.areas.reference [m^2]
Other changes to vertical_stabilizer (see wing_planform)
Properties Used:
N/A
"""
vertical_stabilizer.areas.reference = wing.spans.projected*c_vt*wing.areas.reference/l_vt
wing_planform(vertical_stabilizer)
return 0