In this article, a method for calculation of air Spektra Direkt 2 Crossover loads of an aircraft with an elastic wing is presented.The method can predict a redistribution of air loads when the elastic wing deforms.Unlike the traditional Euler or Navier-Stokes CFD to FEM coupling, the method uses 3D panel method as a source of aerodynamic data.
This makes the calculation feasible on a typical recent workstation.Due to a short computational time and low hardware demands this method is suitable for both the preliminary design stage and the load evaluation stage.A case study Card Case is presented.
The study compares a glider wing performing a pull maneuver at both rigid and and elastic state.The study indicates a significant redistribution of air load at the elastic case.