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35 Aerodynamics Design using vortex lat- tice/boundary layer codes; some CFD for analy- sis [51, 85, 158] CFD results from similar con- figuration, with increment for BLI [56] L/D correction meth- ods from Toren- beek [16] Structures NA 6 DOF beam FEM [158] NA NA (for MDAO); detailed analysis of split-wing pub- lished in NASA report WATE for fan weight [81]; low-fidelity radiator model; tops-down empirical for all others NA Weights FLOPS tops-down methods Parametric wing weight (from Raymer) [51], sized beam model [158] WATE for propulsion flow- paths; tops-down kg/kW es- timates for electrics/TMS [90, 91] Semi-empirical struc- tural methods; tops- down kg/kW methods for electrics [20] GNC Engine, motor, TMS control variables for on- and off-design anal- ysis Full-mission optimal con- trol [141] NA; some discussion of off- design conditions in [57] NA NA Electrical Moderate fidelity motor/inverter loss modeling; equivalent- circuit battery Transient battery model based on Thevenin equiv. circuits (cell-level). Assumed efficien- cies for wire/motors [141] Conceptual: efficiency stackup method with estimates for fu- ture tech. Transient: RLC circuit model in SimPowerSys- tems [90, 95] Efficiency stackup; battery model unclear Low-fidelity efficiency stackup with empiri- cal battery discharge curve [20] Turbo/Propulsion NPSS Propeller map from manuf.; prop efficiency from the- ory [141], blade element momentum theory [158] Analytical model for optimiza- tion; thermal FEM of mo- tor [141, 153] NPSS [59] 2D fan analysis using ve- locity triangles [81]; effi- ciency maps for turboma- chinery Single prop efficiency parameter [20] Thermal TMS sizing considering various heat sources and types of heat sinks NA except for fuel/energy Coolant system load based on efficiency stackup (assume 100% to heat) [90] NA Cooling based on flight cond. [79]; TMS model dis- cussed in [119] NA NA Cash operating cost NA except for fuel/energy Considers relative cost of fuel/elec; cash oper- ating cost [25] NA Ownership cost Noise NA NA NA ANOPP noise simulation prompted redesign [91] FMEA and FTA for loss of thrust; more work needed for other hazards [94, 96] NA Safety Comprehensive FMEA [52, 53] Qualitative GT-HEAT [142, 154, 164] FLOPS/drag polar; BLI benefit based on flat-plate momentum thickness NASA X-57 NASA N-3X ESAero [67] Drag polar Bauhaus Luftfahrt NA NA NA NA NA NA Table 6: Electric aircraft modeling and simulationPDF Image | Electric, hybrid, and turboelectric fixed-wing aircraft
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