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An Aircraft Design Toolbox
This PR separates the code that deflects control surface panels from generate_wing_vortex_distribution, making it a standalone function. After generating all other surfaces (VLM_wings, fuselages, nacelles), generate_vortex_distribution then calls this function.
This PR updates the interpolation range for the airfoil surrogates. It also consolidates the read process of the airfoil polar data, and enables non-xfoil polar data to be read in...
# Pull Request Checklist * Merge in the latest Develop branch changes to your branch * Remove .pyc files from your repository: * Linux/Mac * find . -name *.pyc -delete...
This PR primarily comprises two functions - prop_rotor_design.py and lift_rotor_design.py I also cleaned up and renamed the regression test to be more inclusive of the tests conducted
l. 370-372: Acc. to p.75 in the SAE ARP876 report, GPROX should be subtracted from SPL_m and not added. 
1. l. 76, 107 & 141: the diameter should be divided by 20 and not 200 acc. to p.73 in SAE ARP876.  2. l.94 & 104: The las part...
l. 55: PG_s is normalized by the mixed jet diameter and not the secondary diameter acc. to p.74 in SAE ARP876. 
Is there a reason why the vertical tail noise is not included in SPL_total in noise_airframe_Fink.py l.189 + 190? # Total Airframe Noise SPL_total = 10.*np.log10(10.0**(0.1*SPL_wing)+10.0**(0.1*SPLht)+10**(0.1*SPL_flap)+ \ 10.0**(0.1*SPL_slat)+10.0**(0.1*SPL_main_landing_gear)+10.0**(0.1*SPL_nose_landing_gear))
1. Comparing the equation for G2 for n_wheels==1 or n_wheels==2 in noise_landing_gear with the equation from the original source, I fell like the parenthesis are not correct. Instead of: G2...
Suggest outputting only vert tail weight, not a Data structure to match wing_main.py and tail_horizontal.py convention Change "return output" to "return tail_vert_English * Units.lbs"
