Performance Evaluation of Attached Inflatable Decelerators with Mechanically Deployed Inlets at Mach Numbers from 2.6 to 4.4
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
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A test was conducted in the 16-ft Propulsion Wind Tunnel 16S to determine the effect of reducing the inlet capture area on the deployment and performance characteristics of attached inflatable decelerators. Because of malfunctions of the inlet deployment mechanism, limited deployment data were obtained on only one of the decelerator models. Decreasing the inlet capture area increased the inflation time to 2.2 sec but resulted in poor decelerator inflation and low drag coefficient compared with previous AID models tested.
- Unmanned Spacecraft