7.16. Propeller selection (student version)

Written by Marc Budinger (INSA Toulouse), Scott Delbecq (ISAE-SUPAERO) and Félix Pollet (ISAE-SUPAERO), Toulouse, France.

7.16.1. Design graph

The following diagram represents the design graph of the propeller’s selection. The max thrust is assumed to be known here.

Fig. 7.19 Propeller design graph

7.16.1.1. Sizing code

import numpy as np

# Specifications
rho_air = 1.18  # [kg/m^3] Air density
ND_max = 105000.0 / 60.0 * 0.0254  # [Hz.m] Max speed limit (N.D max) for APC MR propellers

# Reference parameters for scaling laws
D_pro_ref = 11.0 * 0.0254  # [m] Reference propeller diameter
M_pro_ref = 0.53 * 0.0283  # [kg] Reference propeller mass

# Assumptions
F_pro_to = 15.0  # [N] Thrust for 1 propeller during Take Off
F_pro_hov = 5.0  # [N] Thrust for 1 propeller during hover

# Design variables

## To be completed

# Equations
## To be completed

%whos

Variable    Type      Data/Info
-------------------------------
D_pro_ref   float     0.2794
F_pro_hov   float     5.0
F_pro_to    float     15.0
M_pro_ref   float     0.014999
ND_max      float     44.449999999999996
np          module    <module 'numpy' from '/op<...>kages/numpy/__init__.py'>
rho_air     float     1.18

7.16.1.2. Optimization

# Reference battery parameters for scaling laws
M_bat_ref=0.273 # [kg] Reference mass of battery
E_bat_ref=133200 # [J] Reference Energy of battery
P_max_ref=1850 # [W] Reference max power of battery