Add force to pressure grpahs
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Cal Wing
parent
a794c47d1a
commit
29c11bab72
153
main.py
153
main.py
@ -59,10 +59,34 @@ def make_pressure_graph(sheet1, aoa, rpm, air_speed, doGraph=True):
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#print(pressure)
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#print(pressure.min(), pressure.max())
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# Do the trapiztoal rule integration
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da = []
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for i, _ in enumerate(pressure):
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if i in [0]: continue # Skip 0
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if i in [10]: # Force tapping 11 to use tapping 1 rather then 0
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da.append(((PITOT_PLACEMENT_CHORD_NORM[i] - PITOT_PLACEMENT_CHORD_NORM[0])/2) * (pressure.iloc[0] + pressure.iloc[i]))
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continue
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da.append(((PITOT_PLACEMENT_CHORD_NORM[i] - PITOT_PLACEMENT_CHORD_NORM[i-1])/2) * (pressure.iloc[i-1] + pressure.iloc[i]))
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da = np.array(da)
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#print("\n\n\n\n")
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#print(da)
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#print("\n\n\n\n")
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upper_force = da[:10].sum()
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lower_force = da[10 :].sum()
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force = lower_force - upper_force # Upper Sum (1-10) less Lower Sum (11-19)
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lift = force * cos(aoa)
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drag = force * sin(aoa)
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# Extrapolate Aerofoil Tip
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p1 = (PITOT_PLACEMENT[9], pressure.iloc[9])
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p2 = (PITOT_PLACEMENT[18], pressure.iloc[18])
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pN = (0.9*CHORD_LEN, p2[1] + (p1[1]-p2[1])/2)
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pN = (1.1*max(PITOT_PLACEMENT), p2[1] + (p1[1]-p2[1])/2)
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#print(aoa, rpm, p1[1], p2[1], (p1[1]-p2[1])/2, pN[1], pN[1] > p1[1])
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@ -94,14 +118,14 @@ def make_pressure_graph(sheet1, aoa, rpm, air_speed, doGraph=True):
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# Draw Points & text
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{"x":PITOT_PLACEMENT, "y":pressure, "label":"Pressure Data", "type":"scatter", "args":{"zorder":2}},
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{"label":[str(i) for i in range(1, len(PITOT_PLACEMENT)+1)], "x":PITOT_PLACEMENT, "y":pressure, "type":"annotate"},
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{"type":"text", "x": 0.98, "y": 0.02, "text": f"Min: {pressure.min():.3f} Pa\nMax: {pressure.max():.3f} Pa", "align": ('bottom', 'right')}
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{"type":"text", "x": 0.98, "y": 0.02, "text": f"Min: {pressure.min():.3f} Pa\nMax: {pressure.max():.3f} Pa\nForce: {force:.3f}N\nLift: {lift:.3f}N\nDrag: {drag:.3f}N", "align": ('bottom', 'right')}
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]
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}
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if doGraph:
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makeGraph(graph, False, figSavePath=f'./images/pressure/{{0}}.png', closeFig=True)
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return pressure, graph, (water_density, air_density, atm_presure_inch, pitot_height_inch), (p1, p2, pN)
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return pressure, graph, (water_density, air_density, atm_presure_inch, pitot_height_inch), (p1, p2, pN), aoa, (force, lift, drag, da, upper_force, lower_force)
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def make_cp_graph(pressure, aoa, rpm, air_speed, data, doGraph=True):
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@ -113,30 +137,6 @@ def make_cp_graph(pressure, aoa, rpm, air_speed, data, doGraph=True):
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# Calculate Cp
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cp = pressure / (0.5 * air_density * (air_speed ** 2))
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# Do the trapiztoal rule integration
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da = []
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for i, _ in enumerate(pressure):
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if i in [0]: continue # Skip 0
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if i in [10]: # Force tapping 11 to use tapping 1 rather then 0
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da.append(((PITOT_PLACEMENT_CHORD_NORM[i] - PITOT_PLACEMENT_CHORD_NORM[0])/2) * (pressure.iloc[0] + pressure.iloc[i]))
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continue
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da.append(((PITOT_PLACEMENT_CHORD_NORM[i] - PITOT_PLACEMENT_CHORD_NORM[i-1])/2) * (pressure.iloc[i-1] + pressure.iloc[i]))
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da = np.array(da)
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#print("\n\n\n\n")
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#print(da)
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#print("\n\n\n\n")
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upper_force = da[:10].sum()
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lower_force = da[10 :].sum()
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force = lower_force - upper_force # Upper Sum (1-10) less Lower Sum (11-19)
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lift = force * cos(aoa)
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drag = force * sin(aoa)
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#print("force, lift, drag, upper_force, lower_force")
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#print(force, lift, drag, upper_force, lower_force)
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@ -153,7 +153,7 @@ def make_cp_graph(pressure, aoa, rpm, air_speed, data, doGraph=True):
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graph = {
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"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)",
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"windowTitle": f"Cp along Clark Y 14 Percent Airfoil - Alpha {int(aoa):d} Degrees - {rpm:d}rpm - {air_speed:.1f}m_s",
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"xLabel": "Normalized Pitot Placement",
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"xLabel": "Pitot Placement [m]",
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"yLabel": "$C_p$",
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"grid": True,
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"yLim": (cp.min()-0.5, cp.max()+0.5),
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@ -178,14 +178,14 @@ def make_cp_graph(pressure, aoa, rpm, air_speed, data, doGraph=True):
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# Draw Points & text
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{"x":PITOT_PLACEMENT_CHORD_NORM, "y":cp, "label":"cp Data", "type":"scatter", "args":{"zorder":2}},
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{"label":[str(i) for i in range(1, len(PITOT_PLACEMENT_CHORD_NORM)+1)], "x":PITOT_PLACEMENT_CHORD_NORM, "y":cp, "type":"annotate"},
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{"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')}
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{"type":"text", "x": 0.98, "y": 0.02, "text": f"Min $C_p$: {cp.min():.3f}\nMax $C_p$: {cp.max():.3f}", "align": ('bottom', 'right')}
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]
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}
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if doGraph:
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makeGraph(graph, False, figSavePath=f'./images/cp/{{0}}.png', closeFig=True)
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return cp, (force, lift, drag, da, upper_force, lower_force), graph, (p1, p2, pN), aoa
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return cp, graph, (p1, p2, pN), aoa
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def make_rpm_graph():
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@ -225,14 +225,16 @@ if __name__ == '__main__':
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data = {}
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for raw_data in tqdm((data_508rpm, data_1000rpm), position=0):
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aoa_data = {}
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cp_pain_data = []
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for aoa in tqdm(raw_data["AoA"], position=1):
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sheet = raw_data["data"][f"{aoa} AoA"]
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aoa_data[aoa] = make_pressure_graph(sheet, aoa, raw_data["rpm"], raw_data["airSpeed"], False)
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aoa_data[aoa] = make_pressure_graph(sheet, aoa, raw_data["rpm"], raw_data["airSpeed"], True)
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cp_pain_data.append(aoa_data[aoa])
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data[raw_data["rpm"]] = aoa_data
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if False:
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if True:
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# All
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graph = {
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"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)",
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@ -315,6 +317,36 @@ if __name__ == '__main__':
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makeGraph(graph, False, figSavePath="./images/pressure/__{0}.png")
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if True:
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aoa = [a[-2] for a in cp_pain_data][1::2]
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forces = [a[-1] for a in cp_pain_data][1::2]
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# Force Graphs
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graph = {
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"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)",
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"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",
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"xLabel": "Attack Angle [$\\alpha$]",
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"yLabel": "Force [N]",
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"grid": True,
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"ledgLoc": 1,
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"plots": [
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{"x":aoa, "y":[f[0] for f in forces], "label":"Total Force"},
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{"x":aoa, "y":[f[1] for f in forces], "label":"Lift"},
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{"x":aoa, "y":[f[2] for f in forces], "label":"Drag"},
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]
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}
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makeGraph(graph, False, figSavePath="./images/{0}.png", closeFig=True)
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print("\n\n")
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print(raw_data["rpm"])
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print("AoA Total Lift Drag ---- Upper Force Lower Force ")
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for aoa, force in [(a[-2], a[-1]) for a in cp_pain_data]:
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print(f"{aoa:d}\\textdegree & {force[0]:.3f} & {force[1]:.3f} & {force[2]:.3f} -- {force[4]:.3f} {force[5]:.3f} \\\\")
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print("-"*50)
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print("\n\n")
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print("Generating Cp Graphs")
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cp_data = {}
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@ -333,7 +365,7 @@ if __name__ == '__main__':
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graph = {
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"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)",
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"windowTitle": f"All Cp along Clark Y 14 Percent Airfoil - {raw_data["rpm"]:d}rpm - {raw_data["airSpeed"]:.1f}m_s",
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"xLabel": "Normalized Pitot Placement",
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"xLabel": "Pitot Placement [m]",
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"yLabel": "$C_p$",
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"grid": True,
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"ledgLoc": 1,
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@ -345,7 +377,7 @@ if __name__ == '__main__':
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cp = this_data[0]
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# Extrapolate Aerofoil Tip
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p1, p2, pN = this_data[3]
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p1, p2, pN = this_data[2]
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plts = (
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# Draw Lines
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@ -358,7 +390,7 @@ if __name__ == '__main__':
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{"x": [PITOT_PLACEMENT_CHORD_NORM[9], pN[0]], "y": [cp.iloc[18], pN[1]], "colour": c["color"], "args":{"alpha":0.3}},
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# Draw Points & text
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{"x":PITOT_PLACEMENT_CHORD_NORM, "y":cp, "label":f"α = {int(this_data[4]):d}°", "type":"scatter", "args":{"zorder":2}, "colour": c["color"]},
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{"x":PITOT_PLACEMENT_CHORD_NORM, "y":cp, "label":f"α = {int(this_data[-1]):d}°", "type":"scatter", "args":{"zorder":2}, "colour": c["color"]},
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)
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for plt in plts:
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graph["plots"].append(plt)
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@ -381,7 +413,7 @@ if __name__ == '__main__':
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cp = this_data[0]
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# Extrapolate Aerofoil Tip
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p1, p2, pN = this_data[3]
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p1, p2, pN = this_data[2]
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plts = (
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# Draw Lines
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@ -394,59 +426,12 @@ if __name__ == '__main__':
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{"x": [PITOT_PLACEMENT_CHORD_NORM[9], pN[0]], "y": [cp.iloc[18], pN[1]], "colour": c["color"], "args":{"alpha":0.3}},
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# Draw Points & text
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{"x":PITOT_PLACEMENT_CHORD_NORM, "y":cp, "label":f"α = {int(this_data[4]):d}°", "type":"scatter", "args":{"zorder":2}, "colour": c["color"]},
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{"x":PITOT_PLACEMENT_CHORD_NORM, "y":cp, "label":f"α = {int(this_data[-1]):d}°", "type":"scatter", "args":{"zorder":2}, "colour": c["color"]},
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)
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for plt in plts:
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graph["plots"].append(plt)
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makeGraph(graph, False, figSavePath="./images/cp/__{0}.png", closeFig=True)
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if True:
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aoa = [a[4] for a in cp_pain_data]
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forces = [a[1] for a in cp_pain_data]
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# Force Graphs
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graph = {
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"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)",
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"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",
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"xLabel": "Attack Angle [$\\alpha$]",
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"yLabel": "Force [N]",
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"grid": True,
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"ledgLoc": 1,
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"plots": [
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{"x":aoa, "y":[f[0] for f in forces], "label":"Total Force"},
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{"x":aoa, "y":[f[1] for f in forces], "label":"Lift"},
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{"x":aoa, "y":[f[2] for f in forces], "label":"Drag"},
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]
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}
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makeGraph(graph, False, figSavePath="./images/{0}.png", closeFig=True)
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aoa = [a[4] for a in cp_pain_data][1::2]
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forces = [a[1] for a in cp_pain_data][1::2]
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# Force Graphs
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graph = {
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"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)",
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"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",
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"xLabel": "Attack Angle [$\\alpha$]",
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"yLabel": "Force [N]",
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"grid": True,
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"ledgLoc": 1,
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"plots": [
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{"x":aoa, "y":[f[0] for f in forces], "label":"Total Force"},
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{"x":aoa, "y":[f[1] for f in forces], "label":"Lift"},
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{"x":aoa, "y":[f[2] for f in forces], "label":"Drag"},
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]
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}
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makeGraph(graph, False, figSavePath="./images/{0}.png", closeFig=True)
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if True:
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print("\n\n")
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print(raw_data["rpm"])
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print("AoA Total Lift Drag ---- Upper Force Lower Force ")
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for aoa, force in [(a[4], a[1]) for a in cp_pain_data]:
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print(f"{aoa:d}\\textdegree & {force[0]:.3f} & {force[1]:.3f} & {force[2]:.3f} -- {force[4]:.3f} {force[5]:.3f} \\\\")
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print("-"*50)
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print("\n\n")
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print("Complete")
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