Demo entry 2842798

fun

   

Submitted by anonymous on Oct 15, 2015 at 01:09
Language: Python. Code size: 2.1 kB.

# -*- coding: utf-8 -*-
"""
Created on Fri Oct  9 11:06:53 2015

@author: Aleksandar Petrov
@contact: aleksanndar1995@gmail.com
"""
import numpy as np

def I(f_r, f_l, b, MAC, TOM, boxh, c_root, taper):
    
    halfb=float(b)/2    
    midchord = ChordAtSpanPercent(0.5,c_root,taper)
    
    #fuselage and wings volume
    Vf = np.pi*f_r**2 * f_l
    Vw = halfb*midchord*boxh #for one wing
    
    If = 0.5 * TOM * (float(Vf) / (Vf + 2*Vw) ) * f_r**2
    
    Iw_centroid = (1./12.) * TOM * (float(Vw) / (Vf + 2*Vw)) * (halfb**2 + boxh**2)
    Iw_steiner =  TOM * (float(Vw) / (Vf + 2*Vw)) * (halfb*0.5)**2
    
    I=If+2*(Iw_centroid + Iw_steiner)
    
    return I

def ChordAtSpanPercent(percent, c_root, taper):
    
    c_tip = c_root * taper
    
    return c_tip + (c_root-c_tip)*(1-percent)
    

def DeltaL(dCL, V_inf, SweepLE, ba, bai, b, c_root, taper, rho):
    #velocity seen by wing
    rho = 1.225
    V = V_inf * np.cos(np.deg2rad(SweepLE))
    
    #wing area affecteed by ailerons (for one wing)
    Sa_half = 0.5*(ChordAtSpanPercent(bai, c_root, taper) + ChordAtSpanPercent(ba+bai, c_root, taper) ) * ba * 0.5* b

    DeltaL = dCL * 0.5 * rho * V**2 * Sa_half
    
    return DeltaL
    
    
def L_A(dCL, V_inf, SweepLE, ba, bai, b, c_root, taper, rho):
    
    y_A = (bai+ba*0.5)*b*0.5
    L_A = 2* DeltaL(dCL, V_inf, SweepLE, ba, bai, b, c_root, taper, rho) * y_A
    
    return L_A
    

def y_D(y_D_p,b):
    return y_D_p*b*0.5


def Pss(dCL, V_inf, SweepLE, ba, bai, b, c_root, taper, rho, Stot, C_DR , y_D_p ):
    
    y_D_h = y_D(y_D_p, b)
    L_Ah = L_A(dCL, V_inf, SweepLE, ba, bai, b, c_root, taper, rho)    

    return np.sqrt(float(2*L_Ah)/(rho*Stot*C_DR*y_D_h**3))
    
    
def DeltaD(rho,P,b,y_D_p, Stot, C_DR):
    
    VR = P* y_D(y_D_p, b)
    DeltaD=0.5 * rho*VR**2 * Stot * C_DR
    
    return DeltaD
    
    
def Pdot(dCL, V_inf, SweepLE, ba, bai, b, c_root, taper, rho,P,y_D_p, Stot, C_DR, f_r, f_l, MAC, TOM, boxh):
    
    return ( L_A(dCL, V_inf, SweepLE, ba, bai, b, c_root, taper, rho) - DeltaD(rho,P,b,y_D_p, Stot, C_DR) *  y_D(y_D_p, b)) / I(f_r, f_l, b, MAC, TOM, boxh, c_root, taper)

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