diff --git a/main.py b/main.py
index c356ca6..c591130 100644
--- a/main.py
+++ b/main.py
@@ -25,7 +25,7 @@ for folder in folders:
 INCH_TO_M = 0.0254
 GRAVITY = 9.81 #m/s^2
 
-CHORD_LEN = 90 #mm
+CHORD_LEN = 1000 #90 #mm
 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
 
@@ -116,19 +116,37 @@ def make_cp_graph(pressure, aoa, rpm, air_speed, data, doGraph=True):
     # Do the trapiztoal rule integration
     da = []
     for i, _ in enumerate(pressure):
-        if i in [0, 10]: continue # Skip 0 & Tapping 11 (Don't want to calc taping[11] - tapp[10])
-        da.append(((pressure.iloc[i-1] + pressure.iloc[i])/2) * (PITOT_PLACEMENT_CHORD_NORM[i]-PITOT_PLACEMENT_CHORD_NORM[i-1]))
+        if i in [0]: continue # Skip 0
+        if i in [10]: # Force tapping 11 to use tapping 1 rather then 0
+            da.append(((PITOT_PLACEMENT_CHORD_NORM[i] - PITOT_PLACEMENT_CHORD_NORM[0])/2) * (pressure.iloc[0] + pressure.iloc[i]))
+            continue
+
+        da.append(((PITOT_PLACEMENT_CHORD_NORM[i] - PITOT_PLACEMENT_CHORD_NORM[i-1])/2) * (pressure.iloc[i-1] + pressure.iloc[i]))
+
 
     da = np.array(da)
 
-    force = da.sum()
+    #print("\n\n\n\n")
+    #print(da)
+    #print("\n\n\n\n")
+
+    upper_force = da[:10].sum()
+    lower_force = da[10 :].sum()
+
+    force = lower_force - upper_force # Upper Sum (1-10) less Lower Sum (11-19)
     lift = force * cos(aoa)
     drag = force * sin(aoa)
 
+    #print("force, lift, drag, upper_force, lower_force")
+    #print(force, lift, drag, upper_force, lower_force)
+
+
+    #print(f"{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)
+    pN = (1.1*max(PITOT_PLACEMENT_CHORD_NORM), 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])
 
 
@@ -167,7 +185,7 @@ def make_cp_graph(pressure, aoa, rpm, air_speed, data, doGraph=True):
     if doGraph:
         makeGraph(graph, False, figSavePath=f'./images/cp/{{0}}.png', closeFig=True)
     
-    return cp, (force, lift, drag, da), graph, (p1, p2, pN), aoa
+    return cp, (force, lift, drag, da, upper_force, lower_force), graph, (p1, p2, pN), aoa
 
 
 def make_rpm_graph():
@@ -200,7 +218,7 @@ def make_rpm_graph():
 
 if __name__ == '__main__':
     print("Generating RPM Graph")
-    make_rpm_graph()
+    #make_rpm_graph()
     print("Generated")
 
     print("Loading Data & Generating Pressure Graphs")
@@ -210,11 +228,11 @@ if __name__ == '__main__':
         for aoa in tqdm(raw_data["AoA"], position=1):
             sheet = raw_data["data"][f"{aoa} AoA"]
 
-            aoa_data[aoa] = make_pressure_graph(sheet, aoa, raw_data["rpm"], raw_data["airSpeed"], True)
+            aoa_data[aoa] = make_pressure_graph(sheet, aoa, raw_data["rpm"], raw_data["airSpeed"], False)
 
         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)", 
@@ -424,8 +442,9 @@ if __name__ == '__main__':
         if True:
             print("\n\n")
             print(raw_data["rpm"])
+            print("AoA         Total    Lift      Drag    ---- Upper Force     Lower Force ")
             for aoa, force in [(a[4], a[1]) for a in cp_pain_data]:
-                print(f"{aoa:d}\\textdegree  & {force[0]:.3f} & {force[1]:.3f} & {force[2]:.3f}       \\\\")
+                print(f"{aoa:d}\\textdegree  & {force[0]:.3f} & {force[1]:.3f} & {force[2]:.3f}  -- {force[4]:.3f}    {force[5]:.3f}     \\\\")
             print("-"*50)
             print("\n\n")