Abstract
Payload Fairing protects a spacecraft from temperature heating during the initial launch stages in region of dense atmosphere. Shock waves are formed in the transonic region of flow, which makes the faring the most unstable in this phase. This paper aims at studying and reducing the unsteady pressure levels and hence also the aero acoustic loading in the transonic region i.e. Mach number 0.7 to 1.2. The separation area as well as the shock strength must be reduced. For this reason, flow stimulation to study pressure distribution, shock strength and separation was carried out. The Mach number at which the minimum flow separation as well as the shock strength is the most preferable one.
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