Theoretical and Experimental Dynamic Loads for a Prismatic Float Having an Angle of Dead Rise of 22.5 deg

Abstract

An application of hydrodynamic impact theory as modified at the NACA is presented. Plots which give the maximum load, the time to maximum load, and the variation of the load with time for a prismatic float of 22.5 deg dead rise are given. Curves are given which cover the range of trim angle and flight-path angle for conventional airplanes. Data obtained in the Langley impact basin are used to establish the validity of these computed curves.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1945
Accession Number
ADA801129

Entities

People

  • Wilbur L. Mayo

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautics
  • Agreements
  • Aircrafts
  • Airplanes
  • Angular Acceleration
  • Dynamic Loads
  • Dynamic Response
  • Equations
  • Experimental Data
  • Flight
  • Flight Paths
  • Floats
  • Flying Boats
  • Impact Loads
  • Landing Impact
  • Seaplane Floats
  • Seaplanes

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Marine Hydrodynamics

Technology Areas

  • Space