MINIMUM PRESSURE ENVELOPES FOR MODIFIED NACA-66 SECTIONS WITH NACA A=0.8 CAMBER AND BUSHIPS TYPE 1 AND TYPE 2 SECTIONS

Abstract

Minimum pressure envelopes, computed for steady two-dimensional flow, with an empirical correction for viscosity, are presented in graphic form for three foils: NACA 66 (TMB modified nose and tail) thickness with the NACA a = 0.8 camberline, the BuShips Type I section and the BuShips Type II section. In addition, design charts for selecting an 'optimum' foil are included. A comparison of these foils, designed to have a favorable operating range of minimum pressures for a specified cavitation number and lift coefficient, shows the 66 (modified) form to provide a slightly wider margin for angle changes. Also with zero camber, the 66 (modified) section has a greater range of favorable minimum pressures than the other foils.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1966
Accession Number
AD0629379

Entities

People

  • Terry Brockett

Tags

Communities of Interest

  • Ground and Sea Platforms
  • Materials and Manufacturing Processes

DTIC Thesaurus Topics

  • Abstracts
  • Angle Of Incidence
  • Computer Programs
  • Geometry
  • Leading Edges
  • Model Basins
  • Model Tests
  • Pressure Distribution
  • Propeller Blades
  • Research Facilities
  • Reynolds Number
  • Static Pressure
  • Test And Evaluation
  • Thickness
  • Thin Wings
  • Trailing Edges
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Business Analytics
  • Naval Architecture and Marine Engineering.