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# This file is part of Marius Peter's airfoil analysis package (this program).
#
# This program is free software: you can redistribute it and/or modify
# it under the terms of the GNU General Public License as published by
# the Free Software Foundation, either version 3 of the License, or
# (at your option) any later version.
#
# This program is distributed in the hope that it will be useful,
# but WITHOUT ANY WARRANTY; without even the implied warranty of
# MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
# GNU General Public License for more details.
#
# You should have received a copy of the GNU General Public License
# along with this program. If not, see <https://www.gnu.org/licenses/>.
from math import sin, cos, atan, sqrt
def get_total_mass(*component):
total_mass = float()
for _ in component:
total_mass += _.mass
return total_mass
def lift_rectangular(lift, semi_span):
L_prime = lift / (semi_span * 2)
return L_prime
def lift_elliptical(L_0, y, semi_span):
L_prime = L_0 * sqrt(1 - (y / semi_span) ** 2)
return L_prime
def get_centroid(airfoil):
area = airfoil.stringer.area
numerator = float()
for _ in airfoil.stringer.x_u:
numerator += _ * area
for _ in airfoil.stringer.x_l:
numerator += _ * area
# denominator
# z_c =
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