1. 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): doi: /
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°

2. 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): doi: /
Figure Legend:
Integrated mission analysis numerical procedure flowchart

3. 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): doi: /
Figure Legend:
Resonance chart for the SA330 helicopter main rotor blades—comparison with camrad results from Ref. [20]

4. 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): doi: /
Figure Legend:
Normalized mode shapes for the SA330 helicopter articulated rotor blades: (a) flap modes; (b) lag modes; and (c) torsion modes

5. 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): doi: /
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

6. 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): doi: /
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

7. 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): doi: /
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

8. 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): doi: /
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

9. 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): doi: /
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

10. 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): doi: /
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

11. 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): doi: /
Figure Legend:
Engine performance trim results for the SA330 helicopter: (a) shaft power Pengine, (b) fuel flow wf

12. 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): doi: /
Figure Legend:
Engine performance trim results for the SA330 helicopter: (a) stator outlet temperature (SOT); (b) specific fuel consumption (SFC)

13. 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): doi: /
Figure Legend:
Search and rescue (SAR) mission: (a) geographical definition; (b) time variations of deployed operational airspeed and AGL altitude

14. 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): doi: /
Figure Legend:
Oil and gas (OAG) mission: (a) geographical definition; (b) time variations of deployed operational airspeed and AGL altitude

15. 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): doi: /
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

16. 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): doi: /
Figure Legend:
Engine performance parameters for the SAR mission: (a) LPC running line; (b) HPC running line

17. 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): doi: /
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

18. 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): doi: /
Figure Legend:
Engine performance parameters for the OAG mission: (a) LPC running line; (b) HPC running line