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Add force & cp graphs

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This commit is contained in:
Cal Wing 2024-08-26 20:07:48 +10:00
parent 8a2c7aca4f
commit bc34667a19
3 changed files with 216 additions and 8 deletions
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5
.vscode/settings.json vendored Normal file
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@ -0,0 +1,5 @@
{
"cSpell.words": [
"trapiztoal"
]
}

11
gen_latex.py Normal file
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@ -0,0 +1,11 @@
import os
root = "images\\pressure"
for path, subdirs, files in os.walk(root):
for name in files:
if "1000rpm" not in name: continue
filePath = os.path.join(path, name)
str = "\\begin{subfigure}{0.45\\linewidth}\n \\centering\n \\includegraphics[width=0.95\\linewidth]{" + filePath.replace("\\", '/') + "}\n \\caption{" + name.replace("Percent", "\\%").replace(".png", "").replace("m_s", "m/s") + "}\n\\end{subfigure}"
print(str)

208
main.py
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@ -12,8 +12,8 @@ from numpy import sqrt
from makeGraph import makeGraph, pltKeyClose, UQ_COLOURS as UQC, uq_colour_cycler_factory as uqccf # Custom Graphing Lib
# Override Sin & Cos to use & return degrees
#def sin(angle): return np.sin(np.deg2rad(angle))
#def cos(angle): return np.cos(np.deg2rad(angle))
def sin(angle): return np.sin(np.deg2rad(angle))
def cos(angle): return np.cos(np.deg2rad(angle))
# Make sure the relevant folders folder exists
#folders = ["./images", "./tmp", "./data"]
@ -26,7 +26,7 @@ INCH_TO_M = 0.0254
GRAVITY = 9.81 #m/s^2
CHORD_LEN = 90 #mm
PITOT_PLACEMENT = np.array((0,4,8,16,25,34,43,53,61,70,5,9,17,25,34,43,53,61,70)) # mm from base of chord
PITOT_PLACEMENT = np.array((0,4,8,16,25,34,43,52,61,70,5,9,17,25,34,43,52,61,70)) # mm from base of chord
PITOT_PLACEMENT_CHORD_NORM = PITOT_PLACEMENT / CHORD_LEN
print("="*15, "Loading Data", "="*15)
@ -68,7 +68,7 @@ def make_pressure_graph(sheet1, aoa, rpm, air_speed, doGraph=True):
graph = {
"title": f"Pressure vs Pitot Placement along Chord\nfor a Clark Y 14% Aerofoil at:\nα = {int(aoa):d}° at {rpm:d} RPM ({air_speed:.1f}m/s)",
"windowTitle": f"Pressure along Clark Y 14% Airfoil - Alpha {int(aoa):d} Degrees - {rpm:d}rpm - {air_speed:.1f}m_s",
"windowTitle": f"Pressure along Clark Y 14 Percent Airfoil - Alpha {int(aoa):d} Degrees - {rpm:d}rpm - {air_speed:.1f}m_s",
"xLabel": "Pitot Placement [mm]",
"yLabel": "Pressure [Pa]",
"grid": True,
@ -104,6 +104,72 @@ def make_pressure_graph(sheet1, aoa, rpm, air_speed, doGraph=True):
return pressure, graph, (water_density, air_density, atm_presure_inch, pitot_height_inch), (p1, p2, pN)
def make_cp_graph(pressure, aoa, rpm, air_speed, data, doGraph=True):
water_density, air_density, atm_presure_inch, pitot_height_inch = data
#print(pressure)
#print(pressure.min(), pressure.max())
# Calculate Cp
cp = pressure / (0.5 * air_density * (air_speed ** 2))
# Do the trapiztoal rule integration
da = []
for i, _ in enumerate(pressure):
if not i: continue # Skip 0
da.append(((pressure.iloc[i-1] + pressure.iloc[i])/2) * (PITOT_PLACEMENT_CHORD_NORM[i]-PITOT_PLACEMENT_CHORD_NORM[i-1]))
da = np.array(da)
force = da.sum()
lift = force * sin(aoa)
drag = force * cos(aoa)
# Extrapolate Aerofoil Tip
p1 = (PITOT_PLACEMENT_CHORD_NORM[9], cp.iloc[9])
p2 = (PITOT_PLACEMENT_CHORD_NORM[18], cp.iloc[18])
pN = (0.9, p2[1] + (p1[1]-p2[1])/2)
#print(aoa, rpm, p1[1], p2[1], (p1[1]-p2[1])/2, pN[1], pN[1] > p1[1])
graph = {
"title": f"$C_p$ vs Pitot Placement along Chord\nfor a Clark Y 14% Aerofoil at:\nα = {int(aoa):d}° at {rpm:d} RPM ({air_speed:.1f}m/s)",
"windowTitle": f"Cp along Clark Y 14 Percent Airfoil - Alpha {int(aoa):d} Degrees - {rpm:d}rpm - {air_speed:.1f}m_s",
"xLabel": "Normalized Pitot Placement",
"yLabel": "$C_p$",
"grid": True,
"yLim": (cp.min()-0.5, cp.max()+0.5),
"plots": [
# Draw Lines
{"x": PITOT_PLACEMENT_CHORD_NORM[:10], "y":cp[:10], "colour": UQC["purple"]},
{"x": PITOT_PLACEMENT_CHORD_NORM[10:], "y":cp[10:], "colour": UQC["purple"]},
{"x": [PITOT_PLACEMENT_CHORD_NORM[0], PITOT_PLACEMENT_CHORD_NORM[10]], "y": [cp.iloc[0], cp.iloc[10]], "colour": UQC["purple"]},
#{"x": [PITOT_PLACEMENT_CHORD_NORM[9], PITOT_PLACEMENT_CHORD_NORM[18]], "y": [cp.iloc[9], cp.iloc[18]], "colour": UQC["purple"]},
# Draw Extrapolated Airfoil Tip
{"x": [PITOT_PLACEMENT_CHORD_NORM[9], pN[0]], "y": [cp.iloc[9], pN[1]], "colour": UQC["aqua"], "label": "Extrapolated Airfoil Tip"},
{"x": [PITOT_PLACEMENT_CHORD_NORM[9], pN[0]], "y": [cp.iloc[18], pN[1]], "colour": UQC["aqua"]},
# Draw Colour Shading
{"x": PITOT_PLACEMENT_CHORD_NORM[:10], "y":cp[:10], "colour": UQC["purple"], "alpha":0.2, "type":"fill"},
{"x": PITOT_PLACEMENT_CHORD_NORM[10:], "y":cp[10:], "colour": "w", "type":"fill"},
{"x":[PITOT_PLACEMENT_CHORD_NORM[0], PITOT_PLACEMENT_CHORD_NORM[10]], "y":[cp.iloc[0], cp.iloc[10]], "colour": "w", "type":"fill"},
{"x": [PITOT_PLACEMENT_CHORD_NORM[9], pN[0]], "y": [cp.iloc[9], pN[1]], "colour": UQC["aqua"], "type":"fill", "alpha":0.2},
{"x":[PITOT_PLACEMENT_CHORD_NORM[9], pN[0]], "y": [cp.iloc[18], pN[1]], "colour": "w", "type":"fill"},
# Draw Points & text
{"x":PITOT_PLACEMENT_CHORD_NORM, "y":cp, "label":"cp Data", "type":"scatter", "args":{"zorder":2}},
{"label":[str(i) for i in range(1, len(PITOT_PLACEMENT_CHORD_NORM)+1)], "x":PITOT_PLACEMENT_CHORD_NORM, "y":cp, "type":"annotate"},
{"type":"text", "x": 0.98, "y": 0.02, "text": f"Min $C_p$: {cp.min():.3f}\nMax $C_p$: {cp.max():.3f}\nForce: {force:.3f}N\nLift: {lift:.3f}N\nDrag: {drag:.3f}N", "align": ('bottom', 'right')}
]
}
if doGraph:
makeGraph(graph, False, figSavePath=f'./images/cp/{{0}}.png', closeFig=True)
return cp, (force, lift, drag, da), graph, (p1, p2, pN), aoa
def make_rpm_graph():
air_density = data_508rpm["data"]["0 AoA"].iloc[1, 2] # kg/m^3
rpm = np.concat((np.array([0]), np.array(data_508rpm["data"]["0 AoA"].iloc[4:14, 2])))
@ -148,11 +214,11 @@ if __name__ == '__main__':
data[raw_data["rpm"]] = aoa_data
if True:
if False:
# All
graph = {
"title": f"Pressure vs Pitot Placement along Chord\nfor a Clark Y 14% Aerofoil at:\n{raw_data["rpm"]:d} RPM ({raw_data["airSpeed"]:.1f}m/s)",
"windowTitle": f"All Pressure along Clark Y 14% Airfoil - {raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m_s",
"windowTitle": f"All Pressure along Clark Y 14 Percent Airfoil - {raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m_s",
"xLabel": "Pitot Placement [mm]",
"yLabel": "Pressure [Pa]",
"grid": True,
@ -202,7 +268,7 @@ if __name__ == '__main__':
makeGraph(graph, False, figSavePath="./images/pressure/__{0}.png")
graph["plots"] = []
graph["windowTitle"] = f"Pressure along Clark Y 14% Airfoil - {raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m_s"
graph["windowTitle"] = f"Pressure along Clark Y 14 Percent Airfoil - {raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m_s"
colour_cycle = uqccf()
for aoa, c in list(zip(aoa_data, colour_cycle))[1::2]:
@ -231,7 +297,133 @@ if __name__ == '__main__':
makeGraph(graph, False, figSavePath="./images/pressure/__{0}.png")
print("Data Loaded")
print("Generating Cp Graphs")
cp_data = {}
for raw_data in tqdm((data_508rpm, data_1000rpm), position=0):
cp_pain_data = []
for aoa in tqdm(raw_data["AoA"], position=1):
this_data = data[raw_data["rpm"]][aoa]
cp_data_this = make_cp_graph(this_data[0], aoa, raw_data["rpm"], raw_data["airSpeed"], this_data[2], False)
cp_pain_data.append(cp_data_this)
cp_data[raw_data["rpm"]] = cp_pain_data
if False:
# All
graph = {
"title": f"All $C_p$ vs Pitot Placement along Chord\nfor a Clark Y 14% Aerofoil at:\n{raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m/s)",
"windowTitle": f"All Cp along Clark Y 14 Percent Airfoil - {raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m_s",
"xLabel": "Normalized Pitot Placement",
"yLabel": "$C_p$",
"grid": True,
"ledgLoc": 1,
"plots": [],
}
colour_cycle = uqccf()
for this_data, c in zip(cp_pain_data, colour_cycle):
cp = this_data[0]
# Extrapolate Aerofoil Tip
p1, p2, pN = this_data[3]
plts = (
# Draw Lines
{"x": PITOT_PLACEMENT_CHORD_NORM[:10], "y":cp[:10], "colour": c["color"]},
{"x": PITOT_PLACEMENT_CHORD_NORM[10:], "y":cp[10:], "colour": c["color"]},
{"x": [PITOT_PLACEMENT_CHORD_NORM[0], PITOT_PLACEMENT_CHORD_NORM[10]], "y": [cp.iloc[0], cp.iloc[10]], "colour": c["color"]},
# Draw Extrapolated Airfoil Tip
{"x": [PITOT_PLACEMENT_CHORD_NORM[9], pN[0]], "y": [cp.iloc[9], pN[1]], "colour": c["color"], "args":{"alpha":0.3}},
{"x": [PITOT_PLACEMENT_CHORD_NORM[9], pN[0]], "y": [cp.iloc[18], pN[1]], "colour": c["color"], "args":{"alpha":0.3}},
# Draw Points & text
{"x":PITOT_PLACEMENT_CHORD_NORM, "y":cp, "label":f"α = {int(this_data[4]):d}°", "type":"scatter", "args":{"zorder":2}, "colour": c["color"]},
)
for plt in plts:
graph["plots"].append(plt)
if raw_data["rpm"] == 508:
#graph['xLim'] = (
# min(PITOT_PLACEMENT_CHORD_NORM) - 0.5,
# max(PITOT_PLACEMENT_CHORD_NORM) + 0.5
#)
graph["figSize"] = (8, 6)
makeGraph(graph, False, figSavePath="./images/cp/__{0}.png")
graph["title"] = f"$C_p$ vs Pitot Placement along Chord\nfor a Clark Y 14% Aerofoil at:\n{raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m/s)"
graph["windowTitle"] = f"Cp along Clark Y 14 Percent Airfoil - {raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m_s"
graph["plots"] = []
colour_cycle = uqccf()
for this_data, c in list(zip(cp_pain_data, colour_cycle))[1::2]:
cp = this_data[0]
# Extrapolate Aerofoil Tip
p1, p2, pN = this_data[3]
plts = (
# Draw Lines
{"x": PITOT_PLACEMENT_CHORD_NORM[:10], "y":cp[:10], "colour": c["color"]},
{"x": PITOT_PLACEMENT_CHORD_NORM[10:], "y":cp[10:], "colour": c["color"]},
{"x": [PITOT_PLACEMENT_CHORD_NORM[0], PITOT_PLACEMENT_CHORD_NORM[10]], "y": [cp.iloc[0], cp.iloc[10]], "colour": c["color"]},
# Draw Extrapolated Airfoil Tip
{"x": [PITOT_PLACEMENT_CHORD_NORM[9], pN[0]], "y": [cp.iloc[9], pN[1]], "colour": c["color"], "args":{"alpha":0.3}},
{"x": [PITOT_PLACEMENT_CHORD_NORM[9], pN[0]], "y": [cp.iloc[18], pN[1]], "colour": c["color"], "args":{"alpha":0.3}},
# Draw Points & text
{"x":PITOT_PLACEMENT_CHORD_NORM, "y":cp, "label":f"α = {int(this_data[4]):d}°", "type":"scatter", "args":{"zorder":2}, "colour": c["color"]},
)
for plt in plts:
graph["plots"].append(plt)
makeGraph(graph, False, figSavePath="./images/cp/__{0}.png")
if True:
aoa = [a[4] for a in cp_pain_data]
forces = [a[1] for a in cp_pain_data]
# Force Graphs
graph = {
"title": f"All Total, Lift & Drag Forces\nfor a Clark Y 14% Aerofoil at:\n{raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m/s)",
"windowTitle": f"All Total, Lift and Drag Forces for a Clark Y 14 Percent Airfoil - {raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m_s",
"xLabel": "Attack Angle [$\\alpha$]",
"yLabel": "Force [N]",
"grid": True,
"ledgLoc": 1,
"plots": [
{"x":aoa, "y":[f[0] for f in forces], "label":"Total Force"},
{"x":aoa, "y":[f[1] for f in forces], "label":"Lift"},
{"x":aoa, "y":[f[2] for f in forces], "label":"Drag"},
]
}
makeGraph(graph, False, figSavePath="./images/{0}.png")
aoa = [a[4] for a in cp_pain_data][1::2]
forces = [a[1] for a in cp_pain_data][1::2]
# Force Graphs
graph = {
"title": f"All Total, Lift & Drag Forces\nfor a Clark Y 14% Aerofoil at:\n{raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m/s)",
"windowTitle": f"All Total, Lift and Drag Forces for a Clark Y 14 Percent Airfoil - {raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m_s",
"xLabel": "Attack Angle [$\\alpha$]",
"yLabel": "Force [N]",
"grid": True,
"ledgLoc": 1,
"plots": [
{"x":aoa, "y":[f[0] for f in forces], "label":"Total Force"},
{"x":aoa, "y":[f[1] for f in forces], "label":"Lift"},
{"x":aoa, "y":[f[2] for f in forces], "label":"Drag"},
]
}
makeGraph(graph, False, figSavePath="./images/{0}.png")
print("Complete")