def Case3(cd0,
k1,
k2,
V,
Rc,
h,
alpha,
beta,
WS_range=np.arange(5, 300, 1),
g0=9.81):
'''
calculates the wing loading for constant altitude/ speed turn
designing for turn radius
'''
T_W = []
W_S = []
_, _, rho = isa(h)
q = 0.5 * rho * V**2
n = np.sqrt(1 + ((V**2) / (g0 * Rc))**2)
for WS in WS_range:
TW = beta / alpha * (k1 * n**2 * beta / q * WS + k2 * n + cd0 /
(beta / q * WS))
T_W.append(1 / (V * TW))
# T_W.append(TW)
W_S.append(WS)
plt.plot(W_S, T_W, label='Case 3', linewidth=4)
def Case00(cd0,
k1,
k2,
dVdt,
V,
h,
alpha,
beta,
WS_range=np.arange(5, 300, 1),
g0=9.81):
'''
calculates the wing loading for accelerating climb
designing for climb
'''
T_W = []
W_S = []
_, _, rho = isa(h)
q = 0.5 * rho * V**2
n = 1 + dVdt / g0
for WS in WS_range:
TW = q / alpha * (cd0 / WS + k1 * (n * beta / q)**2 * WS + k2 * n *
beta / q) + beta / alpha * (1 + 1 / g0 * dVdt)
T_W.append(1 / (V * TW))
# T_W.append(TW)
W_S.append(WS)
plt.plot(W_S, T_W, label='Case 00', linewidth=4)
def Case8(cd0,
k1,
k2,
V,
dhdt,
CL,
h,
alpha,
beta,
WS_range=np.arange(5, 300, 1)):
'''
calculates the wing loading for service ceiling
designing for maximum altitude
'''
T_W = []
W_S = []
_, _, rho = isa(h)
q = 0.5 * rho * V**2
for WS in WS_range:
TW = beta / alpha * (k1 * beta / q * WS + k2 + cd0 /
(beta / q * WS) + 1 / V * dhdt)
T_W.append(1 / (V * TW))
# T_W.append(TW)
W_S.append(WS)
plt.plot(W_S, T_W, label='Case 8', linewidth=4)
def Case4(cd0,
k1,
k2,
dVdt,
V,
h,
alpha,
beta,
WS_range=np.arange(5, 300, 1),
g0=9.81):
'''
calculates the wing loading for horizontal acceleration
designing for dVdt (acceleration)
'''
T_W = []
W_S = []
_, _, rho = isa(h)
q = 0.5 * rho * V**2
for WS in WS_range:
TW = beta / alpha * (k1 * beta / q * WS + k2 + cd0 /
(beta / q * WS) + 1 / g0 * dVdt)
T_W.append(1 / (V * TW))
# T_W.append(TW)
W_S.append(WS)
plt.plot(W_S, T_W, label='Case 4', linewidth=4)
def noise_heat(xyzsource, d_inch, P_h, T, B, RPM, h):
'''
Calculates the SPL on a set of points.
Also produces heat map of the surroundings
'''
R_ft = 0.0833333333 * d_inch / 2
m = 1
gamma, R, Temp = 1.4, 287, isa(h)[1]
M_t = V_r(RPM, d_inch, 1) * 0.3048 / np.sqrt(gamma * R * Temp)
V_07 = V_r(RPM, d_inch, 0.7)
#Assumption blade area
A_b = 2 / B * 1 / 12
SPLlst = list()
xrange = np.arange(-0.6, 1 + 0.01, 0.01)
yrange = np.arange(-1.6, 1.6 + 0.01, 0.01)
for x in xrange:
for y in yrange:
xyzobserver = [x, y, 0]
S, theta = position(xyzsource, xyzobserver)
p_rn = list()
p_v = list()
for S, theta in zip(S, theta):
#ORDERED ROTATIONAL NOISE PRESSURE AT OBSERVER
rotationp = p_m(m, S, R_ft, P_h, T, B, M_t, theta)
p_rn.append(rotationp)
#VORTEX NOISE AT OBSERVER
vortexSPL = SPL_vortex(A_b, V_07)
vortexSPL_obs = SPL_to_PWL_dist(vortexSPL, 300, S_obs=S)
vortexp = SPL_to_p(vortexSPL_obs)
p_v.append(vortexp)
p_sum = sum(p_rn) + sum(p_v)
SPL = p_to_SPL(p_sum)
if SPL > 120:
SPLlst.append(120)
else:
SPLlst.append(SPL)
SPLlst = np.array(SPLlst).reshape(len(xrange), len(yrange))
window = [yrange[0], yrange[-1], xrange[-1], xrange[0]]
plt.imshow(SPLlst, cmap='Reds', extent=window)
plt.colorbar()
plt.plot(FW_skeleton[1], FW_skeleton[0], "black")
return SPLlst
def Case1(V, h, cd0, alpha, WS_range=np.arange(5, 300, 1)):
'''
calculates the wing loading for constant altitude and speed cruise
designing for cruise speed
'''
T_W = []
W_S = []
_, _, rho = isa(h)
q = 0.5 * rho * V**2
for WS in WS_range:
TW = (q * cd0) / (alpha * WS)
T_W.append(1 / (V * TW))
# T_W.append(TW)
W_S.append(WS)
plt.plot(W_S, T_W, label='Case 1', linewidth=4)
def Case2(cd0, k1, k2, V, h, alpha, beta, WS_range=np.arange(5, 300, 1)):
'''
calculates the wing loading for constant speed climb
designing for climb
'''
T_W = []
W_S = []
_, _, rho = isa(h)
q = 0.5 * rho * V**2
for WS in WS_range:
TW = beta / alpha * (k1 * beta / q * WS + k2 + cd0 /
(beta / q * WS) + 1)
T_W.append(1 / (V * TW))
# T_W.append(TW)
W_S.append(WS)
plt.plot(W_S, T_W, label='Case 2', linewidth=4)
def req_noise(xyzsource, d_inch, P_h, T, B, RPM, h, r, CG, PWL_req):
SPL_req = PWL_to_SPL(PWL_req, r)
print(SPL_req)
SPLlst = list()
R_ft = 0.0833333333 * d_inch / 2
m = 1
gamma, R, Temp = 1.4, 287, isa(h)[1]
M_t = V_r(RPM, d_inch, 1) * 0.3048 / np.sqrt(gamma * R * Temp)
V_07 = V_r(RPM, d_inch, 0.7)
#Assumption blade area
A_b = 2 / B * 1 / 12
thetalst = list()
for theta in np.arange(0, 360 + 1, 1):
x = r * np.sin(theta)
y = r * np.cos(theta)
thetalst.append(theta)
xyzobserver = [x, y, 0]
S, theta = position(xyzsource, xyzobserver)
p_rn = list()
p_v = list()
for S, theta in zip(S, theta):
#ORDERED ROTATIONAL NOISE PRESSURE AT OBSERVER
rotationp = p_m(m, S, R_ft, P_h, T, B, M_t, theta)
p_rn.append(rotationp)
#VORTEX NOISE AT OBSERVER
vortexSPL = SPL_vortex(A_b, V_07)
vortexSPL_obs = SPL_to_PWL_dist(vortexSPL, 300, S_obs=S)
vortexp = SPL_to_p(vortexSPL_obs)
p_v.append(vortexp)
p_sum = sum(p_rn + p_v)
SPL = p_to_SPL(p_sum)
SPLlst.append(SPL)
return max(SPLlst), thetalst, SPLlst
#BUTTERFLY PLOT
#plst=list()
#thetalst=list()
#for theta in np.arange(0,2*np.pi*1.026,0.05):
# p=p_m(1,3,0.645833333075,1.36,12.521858094085683,3, 0.75, theta)
# if p>0:
# thetalst.append(theta)
# plst.append(p)
# else:
# thetalst.append(theta)
# plst.append(-p)
#
#plt.plot(thetalst,plst)
#plt.polar(thetalst,plst)
#plt.show()
#plt.ylabel('p')
#plt.xlabel('theta')