Aerodynamic Characteristics of Several Flexible Decelerators at Mach Numbers from 1.8 to 2.5
ARO INC ARNOLD AFS TN
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A test was conducted in a propulsion wind tunnel to determine the aerodynamic performance of four types of decelerators. Data were obtained at Mach numbers from 1.8 to 2.5 at free-stream dynamic pressures from 80 to 200 psf. Increasing the Mach number resulted in a decrease in the steady-state drag coefficient and an increase in the dynamics of the cross parachutes. At Mach number 2.5, increasing the free-stream dynamic pressure resulted in a decrease in the dynamics and an increase in the steady-state drag coefficient of the Supersonic X parachute.
- Lighter-than-air Aircraft