def surfaceSmooth(self, nIter, stepSize, surfFile=None):
"""
Run smoothing iterations on the body surface
Parameters
----------
nIter : int
Number of iterations to run
stepSize : float
Size of step. Must be < 1. Usually less than 0.1 for stability
reasons.
"""
if surfFile is not None:
try:
from pygeo import pyGeo
except:
raise Error(
"pyGeo must be available to use the surface "
"reprojection object. Try again without specifying "
"the surfFile option.")
geoSurf = pyGeo('iges', fileName=surfFile)
self.hyp.allocatesurfaces(geoSurf.nSurf)
for iSurf in range(geoSurf.nSurf):
surf = geoSurf.surfs[iSurf]
self.hyp.setsurface(iSurf + 1, surf.ku, surf.kv, surf.tu,
surf.tv, surf.coef.T)
self.hyp.smoothwrap(nIter, stepSize)
def deform_iges():
# =========================================================================
# Set Up pyGeo Object
# =========================================================================
# rst IGES
# ------------------------------ IGES File ------------------------------ #
geo = pyGeo(fileName=input_files + "deform_geometry_wing.igs",
initType="iges")
geo.doConnectivity()
# rst IGES (end)
# Deform Geometry Object and Output
deform_DVGeo(geo)
def deform_plot3d():
# =========================================================================
# Set Up pyGeo Object
# =========================================================================
# rst plot3d
# ----------------------------- Plot3D File ----------------------------- #
geo = pyGeo(fileName=input_files + "deform_geometry_wing.xyz",
initType="plot3d")
geo.doConnectivity()
geo.fitGlobal()
# rst plot3d (end)
# Deform Geometry Object and Output
deform_DVGeo(geo)
def deform_liftingsurface():
# =========================================================================
# Set Up pyGeo Object
# =========================================================================
# rst LiftingSurface
# --------------------- Lifting Surface Definition --------------------- #
# Airfoil file
naf = 10 # number of airfoils
airfoil_list = ["./geo/rae2822.dat"] * naf
# Airfoil leading edge positions
x = np.linspace(0.0, 7.5, naf)
y = np.linspace(0.0, 0.0, naf)
z = np.linspace(0.0, 14.0, naf)
offset = np.zeros(
(naf, 2)) # x-y offset applied to airfoil position before scaling
# Airfoil rotations
rot_x = [0.0] * naf
rot_y = [0.0] * naf
rot_z = [0.0] * naf
# Airfoil scaling
chord = np.linspace(5.0, 1.5, naf)
# Run pyGeo
geo = pyGeo(
"liftingSurface",
xsections=airfoil_list,
scale=chord,
offset=offset,
x=x,
y=y,
z=z,
rotX=rot_x,
rotY=rot_y,
rotZ=rot_z,
tip="rounded",
bluntTe=True,
squareTeTip=True,
teHeight=0.25 * 0.0254,
)
# rst LiftingSurface (end)
# Deform Geometry Object and Output
deform_DVGeo(geo)
def regTest(self, handler):
dirName = os.path.join(baseDir, "../../input_files")
# Airfoil file
airfoil_list = [dirName + "/rae2822.dat"] * 2
naf = len(airfoil_list) # number of airfoils
# Wing definition
# Airfoil leading edge positions
x = [0.0, 7.5]
y = [0.0, 0.0]
z = [0.0, 14.0]
offset = np.zeros(
(naf, 2)) # x-y offset applied to airfoil position before scaling
# Airfoil rotations
rot_x = [0.0, 0.0]
rot_y = [0.0, 0.0]
rot_z = [0.0, 0.0]
# Airfoil scaling
chord = [5.0, 1.5] # chord lengths
# Run pyGeo
wing = pyGeo(
"liftingSurface",
xsections=airfoil_list,
scale=chord,
offset=offset,
x=x,
y=y,
z=z,
rotX=rot_x,
rotY=rot_y,
rotZ=rot_z,
tip="rounded",
bluntTe=True,
squareTeTip=True,
teHeight=0.25 * 0.0254,
)
for isurf in range(wing.nSurf):
wing.surfs[isurf].computeData()
surf = wing.surfs[isurf].data
handler.root_add_val("sum of surface data",
sum(surf.flatten()),
tol=1e-10)
chord = te - le
x = le
z = span * ref_span
mid_y = (up[0] + low[0]) / 2.0
y = -(up + low) / 2 + mid_y
# Scale the thicknesses
toc = -(up - low) / chord
thickness = toc / 0.12
rot_x = np.zeros(naf)
rot_y = np.zeros(naf)
rot_z = np.zeros(naf)
offset = np.zeros((naf, 2))
bwb = pyGeo(
"liftingSurface",
xsections=airfoil_list,
scale=chord,
offset=offset,
thickness=thickness,
bluntTe=True,
teHeight=0.05,
tip="rounded",
x=x,
y=y,
z=z,
)
bwb.writeIGES("bwb.igs")
(naf, 2)) # x-y offset applied to airfoil position before scaling
# Airfoil rotations
rot_x = [0., 0.]
rot_y = [0., 0.]
rot_z = [0., 0.]
# Airfoil scaling
chord = [5.0, 1.5] # chord lengths
#rst Run pyGeo
wing = pyGeo('liftingSurface',
xsections=airfoil_list,
scale=chord,
offset=offset,
x=x,
y=y,
z=z,
rotX=rot_x,
rotY=rot_y,
rotZ=rot_z,
tip='rounded',
bluntTe=True,
squareTeTip=True,
teHeight=0.25 * .0254)
#rst Write output files
wing.writeTecplot('wing.dat')
wing.writeIGES('wing.igs')
wing.writeTin('wing.tin')
# Finally fill in chord-wise with linear edges
for i in range(ncols):
X[i, :] = geo_utils.linearEdge(X[i, 0], X[i, -1], nrows)
# Boundary conditions
ribBC = {
0:{'all':'123456'},
}
# ==============================================================================
# Generate wingbox
# ==============================================================================
# Get surface definition to use for projections
surfFile = 'wing.igs'
geo = pyGeo('iges', fileName=surfFile)
# Initialize pyLayout
layout = pyLayout.Layout(geo,
teList=[],
nribs=ncols,
nspars=nrows,
elementOrder=2,
X=X,
ribBlank=ribBlank,
sparBlank=sparBlank,
topStringerBlank=topStringerBlank,
botStringerBlank=botStringerBlank,
ribStiffenerBlank=ribStiffenerBlank,
minStringer_height = 0.025,
maxStringer_height = 0.025,
rot_x = [0, 0, 0]
rot_y = [0, 0, 0]
rot_z = [0, 0, 2]
offset = np.zeros((naf, 2))
# There are several examples that follow showing many of the different
# combinations of tip/trailing edge options that are available.
# --------- Sharp Trailing Edge / Rounded Tip -------
wing = pyGeo(
"liftingSurface",
xsections=airfoil_list,
scale=chord,
offset=offset,
x=x,
y=y,
z=z,
rotX=rot_x,
rotY=rot_y,
rotZ=rot_z,
kSpan=2,
tip="rounded",
)
wing.writeTecplot("c172_sharp_te_rounded_tip.dat")
wing.writeIGES("c172_sharp_te_rounded_tip.igs")
# --------- Sharp Trailing Edge / Pinched Tip -------
wing = pyGeo(
"liftingSurface",
xsections=airfoil_list,
scale=chord,