A modal aeroelastic analysis combining structural and aerodynamic models is applied to counterrotating propfans to evaluate their structural integrity for wind-tunnel testing. The aeroelastic analysis code is an extension of the 2D analysis code called the Aeroelastic Stability and Response of Propulsion Systems. Rotational speed and freestream Mach number are the parameters for calculating the stability of the two blade designs with a modal method combining a finite-element structural model with 2D steady and unsteady cascade aerodynamic models. The model demonstrates convergence to the least stable aeroelastic mode, describes the effects of a nonuniform inflow, and permits the modification of geometry and rotation. The analysis shows that the propfan designs are suitable for the wind-tunnel test and confirms that the propfans should be flutter-free under the range of conditions of the testing.
Aeroelastic stability analyses of two counter rotating propfan designs for a cruise missile model
AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference ; 1992 ; Dallas, TX, United States
1992-01-01
Conference paper
No indication
English
Experimental investigation of counter-rotating propfan flutter at cruise conditions
Tema Archive | 1993
|Experimental Investigation of Counter-Rotating Propfan Flutter at Cruise Conditions
Online Contents | 1994
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