Scholarlink

Abstract <p>The aerodynamic performance of staggered supersonic biplane airfoils equipped with leading-edge flaps is studied using numerical simulation. A parametric analysis is carried out to estimate the effects of the stagger distance and the flap deflection angles on the lift-to-drag ratio, the shock wave interactions, and the overall aerodynamic efficiency. The results show that the optimum stagger configurations significantly reduce the wave drag by up to 18%, while the introduction of leading-edge flaps enhances the lift-to-drag ratio by approximately 22% as compared to the conventional biplane designs without flaps. The optimized flap deflection angles effectively smooth the pressure distributions and delay flow separation, leading to improved aerodynamic stability.</p>

错误：搜索内容不能为空，请输入英文关键词
错误：关键词超出字数限制，请精简
高级检索

Aerodynamic Analysis of a Stagger Supersonic Biplane Airfoil with Leading Edge Flap

  • 期刊论文

  • 发表日期：

    2025年9月29日

查看全文
  • V. K. Patidar,
  • MD. G. Sarwar,
  • S. Joshi,
  • D. Sahoo

摘要

Abstract

The aerodynamic performance of staggered supersonic biplane airfoils equipped with leading-edge flaps is studied using numerical simulation. A parametric analysis is carried out to estimate the effects of the stagger distance and the flap deflection angles on the lift-to-drag ratio, the shock wave interactions, and the overall aerodynamic efficiency. The results show that the optimum stagger configurations significantly reduce the wave drag by up to 18%, while the introduction of leading-edge flaps enhances the lift-to-drag ratio by approximately 22% as compared to the conventional biplane designs without flaps. The optimized flap deflection angles effectively smooth the pressure distributions and delay flow separation, leading to improved aerodynamic stability.