The invention discloses an aircraft fore-body and internal waverider-derived hypersonic inlet integrated design method and relates to an aircraft. The method is characterized in that the method is based on an axisymmetric internal contraction basic flow field; the axisymmetric internal contraction basic flow field only comprises an axisymmetric internal contraction rotary wall surface which is formed by connecting two sections of compression molded lines with different compression angles by the internal contraction basic flow field; after the shape of a separation section outlet is specified, basic flow field flow line tracing in different radial positions is performed on each circumferential plane of an inlet, so as to ensure that the internal contraction basic flow field meets designs of an aircraft fore-body and the hypersonic inlet, and an internal waverider-derived hypersonic inlet integrated device with the fore-body is obtained. The method overcomes the defect that inlet overflow of the traditional inlet is serious due to the action of the fore-body; incoming flow captured by the inlet in full flow is realized; the motor thrust is increased, the overflow resistance is reduced; the working range of the inlet is improved; and the low mach number performance of the inlet is improved.
Aircraft fore-body and internal waverider-derived hypersonic inlet integrated design method
2015-09-16
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / 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 |
European Patent Office | 2024
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