Critical Mach Numbers of Thin Airfoil Sections with Plain Flaps

Abstract

Critical Mach number as function of lift coefficient is determined for certain moderately thick NACA low-drag airfoils. Results, given graphically, included calculations on same airfoil sections with plain flaps for small flap deflections. Curves indicate optimum critical conditions for airfoils with flaps in such form that they can be compared with corresponding results for zero flap deflections. Plain flaps increase life-coefficient range for which critical Mach number is in region of high values characteristic of low-drag airfoils.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1946
Accession Number
ADA800605

Entities

People

  • Max A. Heaslet
  • Otway O'm. Pardee

Organizations

  • National Aeronautics and Space Administration

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aeronautics
  • Aircrafts
  • Airfoils
  • Airframes
  • Boundary Layer
  • Coefficients
  • Deflection
  • Dynamic Pressure
  • Fighter Aircraft
  • Free Stream
  • Load Distribution
  • Low Drag
  • Low Drag Airfoils
  • Mach Number
  • Military Aircraft
  • Pressure Distribution
  • Static Pressure

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.