Generate FDM input files for H-Plane #87
Description
It might be necessary to generate input files for FDM execution. This is how swri does it when there's a wing in the design(Showing snippet just for wings)
for i, x in enumerate(wingComponentNames):
pi = i + 1
fdIn.write("\n! Wing (" + str(pi) + ") is component named: " + wingComponentNames[i] + "\n")
chord = allProperties["Wing_CHORD"][3][i]
span = allProperties["Wing_SPAN"][3][i]
fdIn.write(" wing(" + str(pi) + ")%surface_area = " + str(float(span) / 2.0 * float(chord)) + " \n")
dcl_daoa_slope = allProperties["Wing_dCl_dAoA_Slope"][3][i]
aoa_l0 = allProperties["Wing_AoA_L0"][3][i]
fdIn.write(" wing(" + str(pi) + ")%a = " + dcl_daoa_slope + " \n")
fdIn.write(" wing(" + str(pi) + ")%C_L0 = " + str(-float(dcl_daoa_slope) * float(aoa_l0)) + " \n")
fdIn.write(" wing(" + str(pi) + ")%C_Lmax = " + allProperties["Wing_CL_Max"][3][i] + " \n")
fdIn.write(" wing(" + str(pi) + ")%C_Lmin = -" + allProperties["Wing_CL_Max"][3][i] + " \n")
fdIn.write(" wing(" + str(pi) + ")%C_D0 = " + allProperties["Wing_CD_Min"][3][i] + " \n")
fdIn.write(
" wing(" + str(pi) + ")%k = " + str(1.0 / (3.14159 * 0.85 * float(span) / float(chord))) + " \n")
fdIn.write(" wing(" + str(pi) + ")%C_Dfp = 1 \n")
fdIn.write(" wing(" + str(pi) + ")%bias1 = " + allProperties["Wing_Aileron_Bias"][3][i] + " \n")
fdIn.write(" wing(" + str(pi) + ")%bias2 = " + allProperties["Wing_Flap_Bias"][3][i] + " \n")
# TAB: 8/17/2021: Separate control channels for each wing
fdIn.write(" wing(" + str(pi) + ")%icontrol1 = " + str(num_propellers + (i*2) + 1) + " \n")
fdIn.write(" wing(" + str(pi) + ")%icontrol2 = " + str(num_propellers + (i*2) + 2) + " \n")
fdIn.write(" wing(" + str(pi) + ")%tau_a = " + str(0.4) + " \n")
wingName = wingComponentNames[i]
pointName = wingName + ".PNT0"
p0 = pointDict[pointName]
pointName = wingName + ".PNT1"
p1 = pointDict[pointName]
pointName = wingName + ".WING_CENTER_PT"
pc = pointDict[pointName]
fdIn.write(" wing(" + str(pi) + ")%x = " + str(pc[0]) + "\n")
fdIn.write(" wing(" + str(pi) + ")%y = " + str(pc[1]) + "\n")
fdIn.write(" wing(" + str(pi) + ")%z = " + str(pc[2]) + "\n")
vx = (p0[0] - p1[0])
vy = (p0[1] - p1[1])
vz = (p0[2] - p1[2])
dd = math.sqrt(vx * vx + vy * vy + vz * vz)
if dd > 0:
vx = vx / dd
vy = vy / dd * -1
vz = vz / dd * -1
fdIn.write(" wing(" + str(pi) + ")%nx = " + str(vx) + "\n")
fdIn.write(" wing(" + str(pi) + ")%ny = " + str(vy) + "\n")
fdIn.write(" wing(" + str(pi) + ")%nz = " + str(vz) + "\n")