Spectral　proper　orthogonal　decomposition　(SPOD)　is　performed　on　the　near-stall　tip　leakage　flow　of　a　low-speed　compressor　rotor.　The　data　used　for　the　SPOD　analysis　is　obtained　by　delayed-detached　eddy　simulation　(DDES),　which　is　validated　against　experimental　data.　The　flow　quantities　of　interest　include　the　near-tip　axial　velocity　and　the　blade　surface　pressure.　Results　show　that　the　near-stall　flow　field　of　the　investigated　rotor　is　governed　by　two　tip　leakage　vortices　(TLV).　The　main　TLV　initiated　from　the　leading　edge　exerts　an　unsteady　force　on　the　blade　pressure　surface.　Its　modal　component　is　dominated　by　the　leading　modes　at　low　frequencies.　The　secondary　TLV　originated　from　the　mid-chord　creates　a　weaker　unsteady　force　on　the　blade　suction　surface,　and　its　modal　component　has　more　high-frequency　components　due　to　its　interaction　with　the　suction　surface　boundary　layer　flows.　These　findings　improve　the　understanding　of　the　effects　of　tip　leakage　flow　on　compressor　aerodynamic　and　aeroelastic　stability.　Copyright　©　2021　by　the　Authors.