DEVELOPMENT OF AERO-THERMODYNAMIC PROCEDURES FOR DESIGNING HIGH SPEED VEHICLE LEADING EDGES,

Abstract

Aerodynamic and thermodynamic procedures were developed for analyzing and designing heat-sustaining leading edges and forebodies of highspeed aircraft and missiles. A series of design charts is presented for symmetrical, blunted wedge, and conical leading edges that enable the user to predict steady state surface temperature distributions of radiation-cooled nose sections while considering aerodynamic drag. The methods and design charts apply to flight speeds between Mach 2 and Mach 24, and altitudes between sea level and 220,000 feet. In adition, a sample structural analysis was conducted for two different leading edge shapes of a swept wing being maintained at a flight condition of Mach 3.5 at 80,000 feet altitude. The results apply to aircraft, missiles and glide reentry vehicles operating under quasi-steady flight conditions. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1943
Accession Number
AD0431275

Entities

People

  • J. K. Mccullough

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Drag
  • Aircrafts
  • Altitude
  • Flight Speeds
  • Leading Edges
  • Reentry Vehicles
  • Sea Level
  • Steady State
  • Structural Analysis
  • Surface Temperature
  • Swept Wings
  • Vehicles

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.