A low-speed wind-tunnel test was performed with a 3%-scale model of a booster rocket mated to an X-43A research vehicle, a combination referred to as the Hyper-X launch vehicle. The test was conducted both in freestream air and in the presence of a partial model of the B-52B airplane. The objectives of the test were to obtain force and moment data to generate structural loads affecting the pylon of the B-52B airplane and to determine the aerodynamic influence of the B-52B on the Hyper-X launch vehicle for evaluating launch separation characteristics. The windtunnel test was conducted at a low-speed wind tunnel in Hampton, Virginia. All moments and forces reported are based either on the aerodynamic influence of the B-52B airplane or are for the Hyper-X launch vehicle in freestream air. Overall, the test showed that the B-52B airplane imparts a strong downwash onto the Hyper-X launch vehicle, reducing the net lift of the Hyper-X launch vehicle. Pitching and rolling moments are also imparted onto the booster and are a strong function of the launch-drop angle of attack.
Wind-Tunnel Results of the B-52B with the X-43A Stack
2007
7 pages
Report
Keine Angabe
Englisch
Wind-Tunnel Results of the B-52B with the X-43A Stack
AIAA | 2007
|Wind Tunnel Results of the B-52B with the X-43A Stack
Online Contents | 2007
|Wind Tunnel Results of the B-52B with the X-43A Stack
British Library Conference Proceedings | 2006
|Wind Tunnel Results of the B-52B with the X-43A Stack
NTIS | 2006
|Wind Tunnel Results of the B-52B with the X-43A Stack
NTRS | 2006
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