Accession Number:

AD0641676

Title:

AERODYNAMIC AND FLIGHT PERFORMANCE ANALYSIS FOR THE NIRO SOUNDING ROCKET,

Descriptive Note:

Corporate Author:

SPACE-GENERAL CORP EL MONTE CALIF

Personal Author(s):

Report Date:

1966-03-01

Pagination or Media Count:

140.0

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

Subject Categories:

  • Unmanned Spacecraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE