NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Aerodynamic Characteristics of a Model of an Inflatable-Sphere Launching Vehicle under Simulated Conditions of Mach Number and AltitudeAn investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel to determine the aerodynamic characteristics in pitch of a two-stage-rocket model configuration which simulated the last two stages of the launching vehicle for an inflatable sphere. Tests were made through an angle-of-attack range from -6 deg to 18 deg at dynamic pressures of 102 and 255 pounds per square foot with corresponding Mach numbers of 1.89 and 1.98 for the model both with and without a bumper arrangement designed to protect the rocket casing from the outer shell of the vehicle.
Document ID
20040006465
Acquisition Source
Langley Research Center
Document Type
Other - NASA Technical Note (TN)
Authors
Robinson, Ross B.
(NASA Langley Research Center Hampton, VA, United States)
Morris, Odell A.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 21, 2013
Publication Date
December 1, 1960
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
L-911
NASA-TN-D-640
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Document Inquiry

Available Downloads

There are no available downloads for this record.
No Preview Available