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Added option '2' for climb requirements, aligning with the extrapolation approach outlined in Steiner et al. (2014). Optimum number of engines for transport aircraft employing electrically powered distributed propulsion. [Eqs. 4 and 5]
Use an n/(n-1) multiplier for requirement type '2'.
Added an extra option for picking climb gradients for a constraint diagram.
Replaced the fixed lapse rates in each function with a parametric one defined by the user in the Constraint Specification File.
Added parametric lapse rates for the respective constraints. Removed extra plotting code.
Updated inputs for SUSAN's constraint diagram.
If any theoretical drag coefficients are less than 0 (due to poor extrapolation), then set them to 0.
Instead of assuming that the turbofan/turboprop engine thrust is lost, get the actual thrust lost from the propulsion system size. This generalizes the prior code to accommodate losses from heterogeneously-sized propulsion systems.
Added different failure modes and their corresponding specific excess power loss fractions.
Added references to the papers that the information was extracted from.
Included other parameters that were not previously listed for modeling.
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Updates to the constraint diagram generation process were made:
Additional changes were made to the existing Constraint Diagram Specification files, detailing where information was extracted from.