AERODYNAMIC AND FLIGHT PERFORMANCE ANALYSIS FOR THE NIRO SOUNDING ROCKET,

Abstract

Contained in the report are the results of systematic calculations of the NIRO vehicle performance capabilities. These capabilities were determined by computing the vehicle trajectory characteristics for various payload weights and configurations. Trajectory parameters are presented as time-histories of velocity, altitude, range, flight path angle, Mach Number, and dynamic pressure. From these data, summary curves are provided giving velocity and altitude at major time points (i.e., stage ignition, burnout, and apogee) as a function of payload weight, and plots showing apogee altitude and impact range as a function of payload weight and launch angle (with constant apogee time lines). A set of data are given for each payload configuration. Also, included for information, are the vehicle weight, propulsion, and drag data used in these computations. (Author)

Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1966
Accession Number
AD0641676

Entities

People

  • A. M. Olson
  • J. P. Taylor

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Altitude
  • Computations
  • Dynamic Pressure
  • Flight
  • Flight Paths
  • Ignition
  • Mach Number
  • Motion
  • Physical Properties
  • Rockets
  • Sounding Rockets
  • Trajectories

Fields of Study

  • Physics

Readers

  • Approximation Theory.
  • Fluid Dynamics.
  • Missile Defense Systems.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster
  • Space - Orbital Debris