diff --git a/.vscode/settings.json b/.vscode/settings.json
new file mode 100644
index 0000000..7a27222
--- /dev/null
+++ b/.vscode/settings.json
@@ -0,0 +1,5 @@
+{
+    "cSpell.words": [
+        "trapiztoal"
+    ]
+}
\ No newline at end of file
diff --git a/gen_latex.py b/gen_latex.py
new file mode 100644
index 0000000..c4391cf
--- /dev/null
+++ b/gen_latex.py
@@ -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)
diff --git a/main.py b/main.py
index d902608..30936a4 100644
--- a/main.py
+++ b/main.py
@@ -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")