In　the　current　study,　a　novel　combination　of　the　aerospike　and　multi-counterflowing-jet　scheme　is　proposed　for　drag　and　heat　reduction　in　high　speed　flight.　The　flow　field　and　aeroheating　characteristics　in　condition　of　large　angle　of　attack　are　quantitatively　investigated　in　a　shock　tunnel.　The　instantaneous　flow　field　structure　and　aeroheating　distribution　are　acquired　using　high-speed　schlieren　technique　and　heat　flux　sensors.　The　experimental　results　reveal　that　the　counterflowing　jets　can　push　the　leading　bow　shock　wave　off　the　model　and　form　a　pair　of　detached　bow　shock　waves.　The　detached　bow　shock　waves　propagate　at　a　constant　velocity　of　about　49.8m/s　and　stop　to　oscillate　ahead　of　the　aerospike.　The　stagnation　region　between　the　detached　bow　shock　wave　and　interface　notably　intensifies　the　local　aeroheating　within　it.　When　it　moves　away,　the　local　aeroheating　is　significantly　alleviated　accordingly.　As　the　counterflowing　jets　start　issuing,　a　high　heat　flux　region　yields　near　the　nozzle　and　moves　upstream.　In　case　of　jets　not　strong　enough　to　push　the　stagnation　region　far　away　from　the　aerospike,　the　local　aeroheating　would　be　intensified　instead　of　reduced.　After　the　detached　bow　shock　waves　stop　propagating　upstream,　the　thermal　load　on　the　windward　part　of　the　blunt　nose　cone　is　reduced　by　more　than　98%.　Basing　on　the　variation　regulation　and　final　position　of　the　high　heat　flux　region,　it　is　suggested　to　rearrange　the　jet　nozzle　along　the　stagnation　ling　to　alleviate　the　aeroheating　more　effectively.　©　2022　Elsevier　Ltd