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Accession Number:
AD0641676
Title:
AERODYNAMIC AND FLIGHT PERFORMANCE ANALYSIS FOR THE NIRO SOUNDING ROCKET,
Corporate Author:
SPACE-GENERAL CORP EL MONTE CALIF
Report Date:
1966-03-01
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
Pages:
0140
Contract Number:
AF 19(628)-5520
File Size:
0.00MB
