Navier–Stokes-Equations-Based Computations of Launch Vehicles Experiencing Forced Coupled Oscillations

Guruswamy, Guru P.

doi:10.2514/1.a33065

“…The OVERFLOW code [10] for Reynoldsaveraged Navier-Stokes (RANS) equations is used to compute the aerodynamic parameters. Grids and time steps are selected based on detailed sensitivity studies similar to that performed by the author in [11,12]. Validation of steady data is made with earlier computations [9].…”

mentioning

confidence: 99%

Dynamic Stability Analysis of Hypersonic Transport During Reentry

Guruswamy

¹

2016

AIAA Journal

Self Cite

2

0

View full text Add to dashboard Cite

Dynamic stability analysis is performed for a typical future hypersonic transport vehicle during atmospheric flight. Unsteady aerodynamic data in the form of indicial responses are generated by solving the Navier-Stokes equations. Computations needed at multiple Mach numbers and associated angles of attack are computed in a single job by using dual-level parallel script. Validity of the indicial approach is established by comparing results with experiment and the time-integration method. Flutter boundaries associated with pitch and heave rigid-body degrees of freedom are computed. Effect of position of the mass center on flutter boundaries, which is more predominant in the transonic regime, is shown. This work advances stability analysis procedures for next-generation hypersonic vehicles. Nomenclature

show abstract

Modeling of 3-DOF Launch Dynamics in Transonic and Supersonic Regime Using Navier-Stokes Equation

Purwar

¹

,

Jagadeesh

²

2019

31st International Symposium on Shock Waves 2

0

View full text Add to dashboard Cite

Dynamic Stability Analysis of Hypersonic Transport during Reentry

Guruswamy

¹

2016

AIAA Atmospheric Flight Mechanics Conference

0

View full text Add to dashboard Cite

Dynamic stability analysis is performed for a typical future hypersonic transport vehicle during atmospheric flight. Unsteady aerodynamic data in the form of indicial responses are generated by solving the Navier-Stokes equations. Computations needed at multiple Mach numbers and associated angles of attack are computed in a single job by using dual-level parallel script. Validity of the indicial approach is established by comparing results with experiment and the time-integration method. Flutter boundaries associated with pitch and heave rigid-body degrees of freedom are computed. Effect of position of the mass center on flutter boundaries, which is more predominant in the transonic regime, is shown. This work advances stability analysis procedures for next-generation hypersonic vehicles.

show abstract

Navier–Stokes-Equations-Based Computations of Launch Vehicles Experiencing Forced Coupled Oscillations

Abstract: = roll axis along longitudinal direction y = yaw axis along zero circumferential angle z = axis perpendicular to x-y plane Φ = phase lead of lateral motion with respect to longitudinal motion matrix ω = 2πf, circular frequency, rad∕s

Cited by 3 publications

References 13 publications

Dynamic Stability Analysis of Hypersonic Transport During Reentry

Dynamic Stability Analysis of Hypersonic Transport During Reentry

Modeling of 3-DOF Launch Dynamics in Transonic and Supersonic Regime Using Navier-Stokes Equation

Dynamic Stability Analysis of Hypersonic Transport during Reentry

Contact Info

Product

Resources

About