Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: WGS 84-based polynomial variations: (a) Cartesian distance corresponding to a minute of latitude dlatmin as a function of the latitudinal coordinate xlat°; (b) Cartesian distance corresponding to a minute of longitude dlongmin as a function of the latitudinal coordinate xlat°

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Integrated mission analysis numerical procedure flowchart

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Resonance chart for the SA330 helicopter main rotor blades—comparison with camrad results from Ref. [20]

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Normalized mode shapes for the SA330 helicopter articulated rotor blades: (a) flap modes; (b) lag modes; and (c) torsion modes

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Flight dynamics trim results for the SA330 helicopter—comparison with flight test data extracted from Ref. [20]: (a) main rotor power required Protor; (b) collective pitch angle θ0

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Flight dynamics trim results for the SA330 helicopter—comparison with flight test data extracted from Ref. [20]: (a) lateral cyclic pitch angle θ1s; (b) longitudinal cyclic pitch angle θ1c

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Unsteady flapwise blade-bending moment for the SA330 helicopter rotor, μ = 0.307—comparison with flight test data extracted from Ref. [20]: (a) r/R = 0.35; (b) r/R = 0.55

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Unsteady flapwise blade bending moment for the SA330 helicopter rotor, μ = 0.321—comparison with flight test data extracted from Ref. [20]: (a) r/R = 0.35, (b) r/R = 0.55

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Unsteady chordwise blade-bending moment for the SA330 helicopter rotor, r/R = 0.73—comparison with flight test data extracted from Ref. [20]: (a) μ = 0.307; (b) μ = 0.321

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Unsteady torsional blade moment for the SA330 helicopter rotor, r/R = 0.33—comparison with flight test data extracted from Ref. [20]: (a) μ = 0.307; (b) μ = 0.321

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Engine performance trim results for the SA330 helicopter: (a) shaft power Pengine, (b) fuel flow wf

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Engine performance trim results for the SA330 helicopter: (a) stator outlet temperature (SOT); (b) specific fuel consumption (SFC)

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Search and rescue (SAR) mission: (a) geographical definition; (b) time variations of deployed operational airspeed and AGL altitude

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Oil and gas (OAG) mission: (a) geographical definition; (b) time variations of deployed operational airspeed and AGL altitude

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Engine performance parameters for the SAR mission: (a) shaft power Pengine – fuel flow wf ; (b) stator outlet temperature SOT – specific fuel consumption SFC

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Engine performance parameters for the SAR mission: (a) LPC running line; (b) HPC running line

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Engine performance parameters for the OAG mission: (a) shaft power Pengine – fuel flow wf; (b) stator outlet temperature SOT – specific fuel consumption SFC

Date of download: 10/30/2017 Copyright © ASME. All rights reserved. From: Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model J. Eng. Gas Turbines Power. 2013;135(9):091201-091201-11. doi:10.1115/1.4024869 Figure Legend: Engine performance parameters for the OAG mission: (a) LPC running line; (b) HPC running line