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Update with new raymer's calcs

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William Johnstone 2024-10-24 17:29:03 +01:00
parent 6d8b15067c
commit 9de36e07e5
1 changed files with 44 additions and 3 deletions
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Raymers Code/raymers.py
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@ -1,4 +1,5 @@
import matplotlib.pyplot as plt import matplotlib.pyplot as plt
import math
def raymers_iterate(current_max_weight, payload_weight, fuel_weight, a_constant, c_constant, variable_sweep_constant): 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) 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') 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 # Add labels to each point
for index, weight in enumerate(metric_estimates): #for index, weight in enumerate(metric_estimates):
plt.text(index, weight + 5, f'{index}: {weight:.2f}', fontsize=9, ha='right') # plt.text(index, weight + 5, f'{index}: {weight:.2f}', fontsize=9, ha='right')
plt.title("Aircraft Raymer's Method Weight Estimation") plt.title("Aircraft Raymer's Method Weight Estimation")
plt.xlabel("Iteration Number") plt.xlabel("Iteration Number")
plt.ylabel("Weight Estimation (g)") plt.ylabel("Weight Estimation (g)")
plt.grid(True) plt.grid(True)
plt.show() #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