Source code for RCAIDE.Library.Methods.Aerodynamics.Common.Drag.lift_wave_drag
# RCAIDE/Library/Methods/Aerodynamics/Common/Drag/lift_wave_drag.py
# (c) Copyright 2023 Aerospace Research Community LLC
#
# Created: Jun 2024, M. Clarke
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# IMPORT
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# RCAIDE imports
from .wave_drag import wave_drag
# package imports
import numpy as np
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# Compressibility Drag Total
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[docs]
def lift_wave_drag(conditions,wing,Sref):
"""Determine lift wave drag for supersonic speeds.
Assumptions:
Source:
Stanford AA241 A/B Course Notes
Args:
conditions.freestream.mach_number (numpy.array): mach number [unitless]
wing.areas.reference (float): wing reference area [m^2]
Sref (float): main wing reference area [m^2]
Returns:
cd_c_l (numpy.array): Wave drag CD due to lift [unitless]
"""
cd_lift_wave = wave_drag(conditions,wing)
mach = conditions.freestream.mach_number
cd_c_l = np.zeros_like(mach)
cd_c_l[mach >= 1.01] = cd_lift_wave[0:len(mach[mach >= 1.01]),0]
cd_c_l = cd_c_l*wing.areas.reference/Sref
return cd_c_l
