Experimental Investigation of a Novel Airframe–Inlet Integrated Full-Waverider Vehicle

In this study, a design methodology is examined for an airframe–inlet integrated full-waverider vehicle that can take advantage of the waverider’s ideal precompression surface for the engine as well as high lift-to-drag ratio characteristics. To validate this design method, a full-waverider vehicle...

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Bibliographic Details
Published in:AIAA journal 2019-07, Vol.57 (7), p.2964-2976
Main Authors: Feng, Ding, Jun, Liu, Chi-Bing, Shen, Zhen, Liu, Shao-Hua, Chen, Wei, Huang
Format: Article
Language:English
Subjects:
Afterbodies
Air flow
Airframes
Angle of attack
Design
Flight conditions
Forebodies
High lift
Mach number
Pressure measurement
Shock waves
Visualization
Wind tunnels
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Summary:In this study, a design methodology is examined for an airframe–inlet integrated full-waverider vehicle that can take advantage of the waverider’s ideal precompression surface for the engine as well as high lift-to-drag ratio characteristics. To validate this design method, a full-waverider vehicle with a cruising Mach number of 6.0 is designed for experiments. Several experiments under both on- and off-design conditions are performed using a wind tunnel. Measurements are obtained using a schlieren and electronic scanning pressure measurement system. The shock wave’s location and shape in the streamwise direction as shown in the schlieren visualization results obtained from the side view indicate that the forebody–inlet of the experimental model maintains the shock-on-lip condition under the specific design flight conditions, thus enabling the inlet to capture efficiently the precompressed air flow. Moreover, the shock wave’s location and shape in the top direction, as shown in the schlieren visualization results obtained from the top view, reveal that both the forebody and afterbody shock waves are attached to the leading edge for the entire length of the experimental model. Furthermore, the pressure distributions along the ramp show that the inlet can be started in the range of angles of attack considered.
ISSN:0001-1452
1533-385X
DOI:10.2514/1.J058126