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| Overview | | Description | | USNEWPAN | | Aeroelastics | | 3D Optimisation | | Free Surface | | For Existing Panel Method Users |


USNEWPAN highlights

  • Unsteady, subsonic, inviscid flow in the frequency domain
  • The governing equation now reduces to a Helmholtz type PDE
  • A logical, significant advance over methods such as DLM
  • Unsteady perturbations to the full NEWPAN steady solution
  • Full support for standard NEWPAN features:
  • thick/thin surfaces, hybrid structured/unstructured etc.
  • Modelling of the effect of incidence and thickness - at any combination of reduced frequency and (subsonic) Mach number
  • Direct coupling to MSC.Nastran™ for flutter analysis

USNEWPAN aeroelastic analysis of a complete aircraft, featuring the unsteady pressure coefficients at a tailplane section throughout the modal oscillation : see more information here

A new, fast, practical capability for flutter analysis, gusts, maneuvering, etc. on complex configurations

A comparison of USNEWPAN with DLM

The Doublet Lattice Method (DLM) is still widely used in the field of aeroelasticity in order to provide the aerodynamic solution during coupled structural analysis. It does, however, feature a number of obvious limitations. A large motivation during the development of USNEWPAN was to provide a practical, more sophisticated, successor to DLM.

USNEWPAN does not rely on the grossly linearized theory of classical methods. Hence the USNEWPAN implementation provides predictions for the effect of thickness and incidence on flutter velocity - an effect not seen with classical methods like DLM. Configurations can be modelled accurately using the true wetted surface, to obtain unsteady results with modest computational time - a few seconds to a few minutes on a typical desktop.

Incidence NO YES
Camber NO YES
Twist NO YES
Thickness NO YES
Frequency domain YES YES
Subsonic YES YES
Transonic NO NO
High Lift NO YES
Fuselage slender body YES
Flutter at trimmed condition NO YES
Easy experimental correction + ++
Ease of use ++ +


USNEWPAN may be run either:
  • stand-alone, producing a set of results for each of the principal rigid body modes, or for a specific user-defined mode; OR
  • coupled to MSC.Nastran™ with results stored directly into the Nastran database.

Please refer to the following pages for more information and validation examples:

Dynamic Aeroelasticity: Flutter Analysis using MSC.Nastran™
USNEWPAN Unsteady Validation: 2D Exact Comparison.
AGARD Report No.702 (LANN wing): USNEWPAN vs Experimental Comparison.

MSC.Nastran,MSC.Patran and MSC.Flightloads are trademarks of MSC.Software Corporation.

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