Calculating Method for Multi-Stage Axial Compressors with Impulse Bladings and Constant Tip Diameter.

Abstract

The report gives an approximate calculating method for the design point performance of multi-stage axial compressors with impulse-type bladings and constant tip diameters. Computing programs for Monroe-1180 programmable calculators are presented to establish the compressor performance and the blading parameters for arbitrary conditions with minimum effort. The report was prepared to permit evaluations of the applicability of such compressors in advanced propulsion units for air-superiority aircraft, or in light-weight lift engines for military VTOL aircraft. (Author)

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1974
Accession Number
AD0778808

Entities

People

  • M. H. Vavra

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerial Warfare
  • Air Power
  • Air Superiority Fighters
  • Aircrafts
  • Calculators
  • Compressors
  • Diameters
  • Fighter Aircraft
  • Military Aircraft
  • Test And Evaluation
  • Vehicles

Fields of Study

  • Engineering

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Computer Science/Computer Engineering/Data Science/Digital Signal Processing.