NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Comparison of predicted and experimental real-gas pressure distributions on space shuttle orbiter nose for shuttle entry air data systemAn experimental investigation of inviscid real-gas effects on the pressure distribution along the Space Shuttle Orbiter nose center line up to an angle of attack of 32 deg was performed in support of the Shuttle Entry Air Data System (SEADS). Free-stream velocities from 4.8 to 6.6 kn/s were generated at hypersonic conditions with helium, air, and CO2, resulting in normal-shock density ratios from 3.7 to 18.4. The experimental results for pressure distribution agreed closely with numerical results. Modified Newtonian theory deviates from both experiment and the numerical results as angle of attack increases or shock density ratio decreases. An evaluation of the use of modified Newtonian theory for predicting SEADS pressure distributions in actual flight conditions was made through comparison with numerical predictions.
Document ID
19800012795
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Shinn, J. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
L-13341
NASA-TP-1627
Accession Number
80N21280
Funding Number(s)
PROJECT: RTOP 506-51-23-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available