Make RPM Graph
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main.py
37
main.py
@ -89,7 +89,38 @@ def make_pressure_graph(sheet1, aoa, rpm, air_speed, doGraph=True):
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return pressure, graph, (water_density, air_density, atm_presure_inch, pitot_height_inch)
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def make_rpm_grpah():
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air_density = data_508rpm["data"]["0 AoA"].iloc[1, 2] # kg/m^3
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rpm = np.concat((np.array([0]), np.array(data_508rpm["data"]["0 AoA"].iloc[4:14, 2])))
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pressure = np.concat((np.array([0]), np.array(data_508rpm["data"]["0 AoA"].iloc[4:14, 4], dtype=np.float64)))
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airSpeed = sqrt(-pressure * 2 / air_density)
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x = np.linspace(rpm[0], rpm[-1], 1000)
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y = 0.0212*x - 0.7751
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graph = {
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"title": f"RPM vs Velocity for Wind Tunnel 3",
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"xLabel": "Fan RPM",
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"yLabel": "Airspeed [m/s]",
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"grid": True,
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"plots": [
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{"x": x, "y":y, "label":"Linear Estimate", "args":{"linestyle":"--"}, "colour": UQC["neutral"]},
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{"type": "scatter", "x":rpm, "y": airSpeed, "label": "Measured Velocity", "colour":UQC["purple"], "args":{"zorder":2}},
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{"type": "point", "x":508, "y": 10, "label": "Selected RPM (508)", "colour":UQC["red"], "zorder":3},
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{"type":"text", "x": 0.98, "y": 0.02, "text": f"Velocity at 508 RPM: {10:.3f} m/s\nVelocity at 1000 RPM: {airSpeed[-1]:.3f} m/s", "align": ('bottom', 'right')},
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{"type":"text", "x": 0.80, "y": 0.85, "text": f"$y = 0.0212 \\cdot x - 0.7751$", "align": ('bottom', 'right'), "facecolour": UQC["neutral"]}
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]
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}
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makeGraph(graph, False, figSavePath='./images/{0}.png')
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if __name__ == '__main__':
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print("Generating RPM Graph")
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make_rpm_grpah()
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print("Loading Data & Generating Pressure Graphs")
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data = {}
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for raw_data in tqdm((data_508rpm, data_1000rpm), position=0):
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@ -97,11 +128,11 @@ if __name__ == '__main__':
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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"], True)
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aoa_data[aoa] = make_pressure_graph(sheet, aoa, raw_data["rpm"], raw_data["airSpeed"], False)
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data[raw_data["rpm"]] = aoa_data
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if True:
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if False:
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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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@ -160,4 +191,6 @@ if __name__ == '__main__':
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