NASA Technical Reports Server (NTRS) 19960054470: Transonic Shock Oscillations And Wing Flutter Calculated With An Interactive Boundary Layer Coupling Method - Info and Reading Options
By NASA Technical Reports Server (NTRS)
"NASA Technical Reports Server (NTRS) 19960054470: Transonic Shock Oscillations And Wing Flutter Calculated With An Interactive Boundary Layer Coupling Method" and the language of the book is English.
“NASA Technical Reports Server (NTRS) 19960054470: Transonic Shock Oscillations And Wing Flutter Calculated With An Interactive Boundary Layer Coupling Method” Metadata:
- Title: ➤ NASA Technical Reports Server (NTRS) 19960054470: Transonic Shock Oscillations And Wing Flutter Calculated With An Interactive Boundary Layer Coupling Method
- Author: ➤ NASA Technical Reports Server (NTRS)
- Language: English
Edition Identifiers:
- Internet Archive ID: NASA_NTRS_Archive_19960054470
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"NASA Technical Reports Server (NTRS) 19960054470: Transonic Shock Oscillations And Wing Flutter Calculated With An Interactive Boundary Layer Coupling Method" Description:
The Internet Archive:
A viscous-inviscid interactive coupling method is used for the computation of unsteady transonic flows involving separation and reattachment. A lag-entrainment integral boundary layer method is used with the transonic small disturbance potential equation in the CAP-TSDV (Computational Aeroelasticity Program - Transonic Small Disturbance) code. Efficient and robust computations of steady and unsteady separated flows, including steady separation bubbles and self-excited shock-induced oscillations are presented. The buffet onset boundary for the NACA 0012 airfoil is accurately predicted and shown computationally to be a Hopf bifurcation. Shock-induced oscillations are also presented for the 18 percent circular arc airfoil. The oscillation onset boundaries and frequencies are accurately predicted, as is the experimentally observed hysteresis of the oscillations with Mach number. This latter stability boundary is identified as a jump phenomenon. Transonic wing flutter boundaries are also shown for a thin swept wing and for a typical business jet wing, illustrating viscous effects on flutter and the effect of separation onset on the wing response at flutter. Calculations for both wings show limit cycle oscillations at transonic speeds in the vicinity of minimum flutter speed indices.
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