ABSTRACT
A combined spike and lateral jet structure was proposed to address the concerns of drag reduction and heat prevention for supersonic aircraft. The CFD approach was used to numerically simulate the configuration's flow field, and its drag reduction and heat prevention capabilities were evaluated. Flow field characteristics, the influence of lateral jet position, and the affect of lateral jet to incoming pressure ratio are among the topics covered in the study. In comparison to a simple spike setup, the following is the study scope: 1. The combined spike and lateral jet configuration's drag reduction and heat prevention process can be characterized as push away, diminish shock wave drag reduction, and low-temperature gas heat prevention. At 0.7, the best drag reduction impact is found, whereas at 0.5, the poorest heatproof effect is seen. 2. The pressure ratio of lateral jet flow to incoming flow has a positive link with drag reduction and heat prevention performance; 3. To obtain the optimum overall drag reduction and thermal efficiency, the ratio of the distance between the jet and the blunt-body to the length of the spike is 0.7, the pressure ratio between the jet and the incoming flow is 0.8. Compared with the single spike, the thermal efficiency is 93.4%, and the drag reduction efficiency is 68.8%.
- Yang Y Z Y J L, Fang D N. Research progress on thermal protection materials and structures of hypersonic vehicles[J]. Applied Mathematics and mechanics (English version), 2008, 29(1): 51-60.Google Scholar
- Schmisseur J D. Hypersonics into the 21st century: A perspective on AFOSR-sponsored research in aerothermodynamics[J]. Progress in aerospace sciences, 2015, 72(Jan.): 3-16.Google Scholar
- Bushnell D M. Shock wave drag reduction[J]. Annual Review of Fluid Mechanics, 2004, 36: 81-96.Google ScholarCross Ref
- Sudarshan B, Jagadeesh G, Saravanan S. Experimental investigation on aerothermal effects of forward-facing cylindrical and parabolic cavity in hypersonic flow[J]. Acta Astronautica, 2021, 185: 226-235.Google ScholarCross Ref
- Zhang R-r, Dong M-z, Huang W Drag and heat flux reduction mechanism induced by the combinational forward-facing cavity and pulsed counterflowing jet configuration in supersonic flows[J]. Acta Astronautica, 2019, 160: 62-75.Google ScholarCross Ref
- Huang W, Chen Z, Yan L Drag and heat flux reduction mechanism induced by the spike and its combinations in supersonic flows: A review[J]. Progress in aerospace sciences, 2019, 105: 31-39.Google Scholar
- Sahoo D, Karthick S K, Das S Parametric Experimental Studies on Supersonic Flow Unsteadiness over a Hemispherical Spiked Body[J]. AIAA Journal, 2020, 58(8): 3446-3463.Google ScholarCross Ref
- Ji C, Liu B, Huang W Investigation on the drag reduction and thermal protection properties of the porous opposing jet in the supersonic flow: A parametric study with constant mass flow rate[J]. Aerospace Science and Technology, 2021, 118:Google ScholarCross Ref
- Jin W. Attached flow formed by opposing jet in hyper/supersonic flow[J]. International Journal of Heat and Mass Transfer, 2019, 141: 905-921.Google ScholarCross Ref
- Das D, Desai S, Kulkarni V Performance assessment of energy deposition based drag reduction technique for Earth and Mars flight conditions[J]. Acta Astronautica, 2019, 159: 418-428.Google ScholarCross Ref
- Meng Y-s, Yan L, Huang W Coupled investigation on drag reduction and thermal protection mechanism of a double-cone missile by the combined spike and multi-jet[J]. Aerospace Science and Technology, 2021, 115:Google ScholarCross Ref
- Zhu L, Li Y, Chen X Hypersonic flow characteristics and relevant structure thermal response induced by the novel combined spike-aerodome and lateral jet strategy[J]. Aerospace Science and Technology, 2019, 95:Google ScholarCross Ref
- Spaid F W, Zukoski E E. A study of the interaction of gaseous jets from transverse slots with supersonic external flows[J]. AIAA Journal, 1968, 6(2): 205-212.Google ScholarCross Ref
Index Terms
- Research on Drag Reduction and Heat Prevention of Supersonic Vehicle with the Composite Configuration of Spike and Lateral Jet
Recommendations
Numerical Investigation of Drag and Heat Flux Reduction in Hypersonic Vehicle with Aerospike
ICCMS '22: Proceedings of the 14th International Conference on Computer Modeling and SimulationTo reduce the aerodynamic and thermal load of hypersonic vehicle, the aerodynamic performance of a blunt body vehicle with a aerospike on its head is studied numerically. The influence of head shape and L/D (length-to-diameter) ratio of aerospike on ...
Influence on Drag Reduction Characteristics of Jet Hole Shape on Bionic Shark Gill Surface
IHMSC '14: Proceedings of the 2014 Sixth International Conference on Intelligent Human-Machine Systems and Cybernetics - Volume 02According to the problem of bionic shark gill jet fluid was able to reduce fluid friction on jet surface, bionic jet surface models were built, which each has different jet hole shape, such as rectangle, arrow-shaped, broken line and other shapes. ...
A PIV Study of a Supersonic Impinging Jet
International Conference on Optical Technology and Image Processing in Fluid, Thermal, and Combustion Flow, Yokohama, Japan, December 1998The characteristics of supersonic impinging jets are investigated using Particle Image Velocimetry (PIV). The purpose of the experiments is to understand the jet induced forces on STOVL aircraft while hovering close to the ground. For this purpose, a ...
Comments