Stability and Control Characteristics of the Winglet Configured KC-135A

Abstract

Using the Boeing FLEXSTAB digital computer system, rigid and elastic models of the winglet configured KC-135A are made. With a rigid analysis, the winglets reduce total drag from 2 to almost 8% with improvements both laterally and longitudinally in static stability. Dynamically, the rigid winglet model is more stable laterally but slightly more oscillatory longitudinally. The lateral dutch roll mode damping ratio increased with winglets from 3 to 12% with only a 3% increase in frequency. Elastic static stability is still improved both laterally and longitudinally with winglets; and dynamically, the winglets improve lateral stability with very little effect longitudinally. With aeroelastic effects, the overall benefit derived from winglet application to the model is less. However, no significant detrimental effects due to winglets are found.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1976
Accession Number
ADA034940

Entities

People

  • Kent R. Crenshaw

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Air Force
  • Aircraft Equipment
  • Aircrafts
  • Airfoils
  • Airframes
  • Commercial Aircraft
  • Computers
  • Control Surfaces
  • Drag Reduction
  • Horizontal Stabilizers
  • Jet Transport Aircraft
  • Plastic Explosives
  • Pressure Distribution
  • Stabilization Systems
  • Transport Aircraft
  • Wing Tips

Readers

  • Control Systems Engineering.
  • Electrical Engineering
  • Unmanned Aerial System (UAS) Autonomous Capabilities and Mission Reconnaissance.