Design and Analysis of Winglets for Military Aircraft. Phase 2

Abstract

A study of the design and analysis of winglets for military aircraft has been completed. This study is a continuation of the work reported in AFFDL- TR-76-6. The program consisted of investigating analytically the AFFDL/Boeing winglet on the take-off and landing configuration of the KC-135A. Also investigated analytically were th effect of a wing leading-edge device on the performance of the AFFDL/Boeing winglet and the design of a compromise high- speed/low-speed winglet. Two wind tunnel tests were conducted by the NASA- Langley Research Center 8-foot transonic tunnel. A high-speed and low-speed test were conducted to determine the effect of the AFFDL/Boeing winglets on the KC-135A's aerodynamic performance and longitudinal and lateral-direction stability. A preliminary plan for a KC-135A winglet retrofit program was developed and its cost estimated. Based on a 1979 program start, the retrofit costs would be recovered by the start of 1984.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1977
Accession Number
ADA046152

Entities

People

  • D. F. Zanton
  • K. K. Ishimitsu

Organizations

  • Boeing

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aircrafts
  • Airfoils
  • Boundary Layer
  • Computer Programs
  • Experimental Data
  • Flow Fields
  • Geometry
  • Horizontal Stabilizers
  • Load Distribution
  • Military Aircraft
  • Pressure Distribution
  • Pressure Gradients
  • Transport Aircraft
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Naval Engineering and Maritime Security