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    • Keywords


      PIV; horseshoe vortex; nose-fairing design; integral method; interference drag.

    • Abstract


      In the context of the wing–fuselage junction flow the purpose of a nose-fairing is to prevent the oncoming boundary-layer flow separation, which in turn eliminates the horseshoe vortex formation at the junction. A simple procedure is proposed here to arrive at an asymmetric fairing shape for a non-zero wing incidence angle. Even though it is a simple method to decide on fairing shape and size, the fairing designed by this method for a wing at 4ͦ incidence is shown to satisfy the purpose of the nose-fairing. The wind tunnel experimental results clearly show that the designed fairing improves the flow quality at the wing–body intersectionby preventing flow separation and vortex formation. Relatively lower momentum deficit in the boundarylayer (behind the wing trailing edge) hints at drag-reduction for the faired configuration.

    • Author Affiliations



      1. CSIR-National Aerospace Laboratories, Bengaluru 560017, India
      2. Academy of Scientific and Innovative Research (AcSIR), Ghaziabad 201002, India
    • Dates

  • Sadhana | News

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