cranfield0001

experiment investig aerodynam wing slipstream experiment studi wing propel slipstream made order determin spanwis distribut lift increas due slipstream differ angl attack wing differ free stream slipstream veloc ratio result intend part evalu basi differ theoret treatment problem compar span load curv togeth support evid show substanti part lift increment produc slipstream due destal boundari layer control effect integr remain lift increment subtract destal lift found agre well potenti flow theori empir evalu destal effect made specif configur experi