The invention discloses a changeable wall surface pressure distribution rule-based osculating flow field ride precursor design method comprising the following steps: S1, determining curves having three kinds of different wall surface pressure distribution rules, wherein the three curves are taken as revolution body generatrices, designing three kinds of different revolution bodies, and solving supersonic velocity axially symmetric flow fields of the three kinds of different revolution bodies, wherein the solved flow fields are taken as standard flow fields having three kinds of different wall surface pressure distribution rules; S2, designing a shock wave outlet line according to the performance requirements of a ride precursor, performing flow field solving in each osculating plane by applying an osculating principle, and combining a three-dimensional standard flow field by all osculating plane flow fields; and S3, determining a projection curve of the edge line of the ride precursor on the bottom, and generating an osculating floe field ride precursor aerodynamic configuration by performing a flow tracking method line in each osculating plane obtained in S2 according to the shock wave outlet line. The ride precursor designed by the method can be used for meeting air inlet channel inlet high pressure rising ratio and can also be used for fully playing a high resistance rising ratio character.
Changeable wall surface pressure distribution rule-based osculating flow field ride precursor design method
2016-02-17
Patent
Elektronische Ressource
Englisch
IPC: | B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
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