A preliminary study investigating the possible variable wing options for the reusable booster of SpaceLiner is described here. This investigation is motivated by a critical condition that arises during the first part of the booster descent, which must be avoided. Based on the previous SpaceLiner 7-3 configuration some modifications on the wing geometry are performed, with the main objective of reducing the wing span. Three wing types are studied here: a fixed wing, a variable sweep wing and a foldable wing. In the study’s first step the geometry of the wing is designed for each of the wing type considered. Mass, centre of gravity and aerodynamic data sets are evaluated with the main purpose of maximizing the aerodynamic performances and keeping the mass as low as possible.