From 9de36e07e529e76e19ec4a4a3869ee96b563b9c6 Mon Sep 17 00:00:00 2001
From: William Johnstone <william@endevrr.com>
Date: Thu, 24 Oct 2024 17:29:03 +0100
Subject: [PATCH] Update with new raymer's calcs

---
 Raymers Code/raymers.py | 47 ++++++++++++++++++++++++++++++++++++++---
 1 file changed, 44 insertions(+), 3 deletions(-)

diff --git a/Raymers Code/raymers.py b/Raymers Code/raymers.py
index 65fdfa4..7586892 100644
--- a/Raymers Code/raymers.py	
+++ b/Raymers Code/raymers.py	
@@ -1,4 +1,5 @@
 import matplotlib.pyplot as plt
+import math
 
 def raymers_iterate(current_max_weight, payload_weight, fuel_weight, a_constant, c_constant, variable_sweep_constant):
     empty_max_weight_ratio =  (a_constant * current_max_weight**c_constant * variable_sweep_constant)
@@ -28,12 +29,52 @@ for imperial_estimate in imperial_estimates:
 
 plt.plot(metric_estimates, linestyle='--', marker='o')
 
+# This section has been commented out because jordan (senft) does not believe the customer wants to see the numbers
 # Add labels to each point
-for index, weight in enumerate(metric_estimates):
-    plt.text(index, weight + 5, f'{index}: {weight:.2f}', fontsize=9, ha='right')
+#for index, weight in enumerate(metric_estimates):
+#    plt.text(index, weight + 5, f'{index}: {weight:.2f}', fontsize=9, ha='right')
 
 plt.title("Aircraft Raymer's Method Weight Estimation")
 plt.xlabel("Iteration Number")
 plt.ylabel("Weight Estimation (g)")
 plt.grid(True)
-plt.show()
\ No newline at end of file
+#plt.show()
+
+print("Raymer's Aircraft Calculations (IMPERIAL UNITS)\n")
+print("Weight Estimation: %0.4f lbs" % imperial_estimates[-1])
+
+# Wing loading 
+typical_weight_area_ratio = 6 # Historical sailplane ratio
+print("Typical Weight Area Ratio: %0.4f lbs/ft^2" % typical_weight_area_ratio)
+
+# To find area of the wings we must work backwards (ratio = weight/area)
+# Area of wings
+wing_area = imperial_estimates[-1] / typical_weight_area_ratio
+print("Main Wing Area: %0.4f ft^2" % wing_area)
+
+# L/D Ratio
+ld_ratio = 7.5 / 1.5
+print("Lift to Drag Ratio: %0.4f" % ld_ratio)
+
+# Aspect Ratio (Wing span) - Need L/D
+aspect_ratio = 4.464 * (ld_ratio**0.69)
+print("Aspect Ratio: %0.4f" % aspect_ratio)
+
+# Wing span
+wing_span = math.sqrt(aspect_ratio*wing_area)
+print("Main Wing Span %0.4f ft" % wing_span)
+
+# Chord Length
+chord_length = wing_area / wing_span
+print("Main Wing Chord Length %0.4f ft" % chord_length)
+
+# Fuselage Length
+fuselage_length = 0.86 * imperial_estimates[-1]**0.48
+print("Fuselage Length %0.4f ft" % fuselage_length)
+
+# Tail Positioning (Moment arm)
+tail_poisitioning = fuselage_length * 0.65
+print("Tail Positioning (Moment arm location) %0.4f ft" % tail_poisitioning)
+
+# Tail Dimensions
+