Subsonic and Transonic Wind Tunnel Testing of Two Inflatable Aerodynamic Decelerators
Author(s)
Tanner, Christopher L.
Cruz, Juan R.
Hughes, Monica F.
Clark, Ian G.
Braun, Robert D.
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Abstract
Two inflatable aerodynamic decelerator designs were
tested in the Transonic Dynamics Tunnel at the
NASA Langley Research Center: a tension cone and
an isotensoid. The tension cone consists of a flexible
tension shell attached to a torus and the isotensoid
employs a ram-air inflated envelope. Tests were
conducted at Mach numbers from 0.3 to 1.08 and
Reynolds numbers from 0.59 to 2.46 million. The
main objective of these tests was to obtain static
aerodynamic coefficients at subsonic and transonic
speeds to supplement supersonic aerodynamic data
for these same two designs. The axial force
coefficients of both designs increased smoothly from
subsonic through transonic Mach numbers. Dynamic
data show significant oscillation of the tension cone
and minimal oscillation of the isotensoid. The
transonic and subsonic data will be used to assemble
an inflatable decelerator aerodynamic database for
use in computational analyses and system studies.
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Date
2010-06
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