Analysis of jet blast impact of embarked aircraft on deck takeoff zone

Chen

Mathematical Problems in Engineering

et al. 2018

The aerodynamic characteristics of the close formation flight are numerically analyzed to facilitate a greater understanding of the vortex effects between UAVs and technically support the application of close formation flight for UAVs. The aerodynamic characteristics of a single UAV are calculated, the results of which are used as the reference to the variation of aerodynamic values in the comparison with close formation flight. The vortex effects of the leading UAV on the aerodynamic characteristics of the trailing UAV in the two UAV close formation flight are analyzed. The position where the trailing UAV obtains the maximum lift-to-drag ratio is defined as the optimal position. Based on the optimal position, three different types of three UAV formations are designed to explore the preliminary application of the aerodynamic benefits in the close formation flight for multiple UAVs. It is observed that the incremental aerodynamic forces and moments of the trailing UAV vary with the lateral and vertical spacing between the two UAVs, and the trailing UAV can obtain significant aerodynamic improvement if positioned at optimal position behind the leading UAV while in close formation flight. It is also proved that the aerodynamic characteristics of the close formation for three UAVs can be improved when the formation is designed based on the optimal position, and this will increase the range and endurance of the UAVs in operational application.

Section: Methodsmentioning

confidence: 99%

Numerical Aerodynamic Characteristics Analysis of the Close Formation Flight

Chen

Mathematical Problems in Engineering

et al. 2018

Mathematical Problems in Engineering

“…Gong et al [30] proposed an improved delay separation vortex simulation (IDDES) method based on the SST model for a high-precision simulation of the jet engine effect and conducted a numerical study of the dynamic jet effect through a RANS/ LES hybrid method. eir results showed that the velocity distribution in a jet blast can be predicted better [31,32].…”

Section: Introductionmentioning

confidence: 93%

Hybrid Numerical Simulation of Jet Blast Distance of a Departing Aircraft

Chang

et al. 2021

A hybrid numerical simulation method was established by combining the Spalart-Allmaras (SA) turbulence model and detached eddy simulation (DES). Numerical simulations were carried out to model cold and hot spray conditions of a nozzle without considering the internal flow of an engine to determine jet conditions. Analysis results show that the calculated hot spray results more in line with the reality. The jet effect of a typical aircraft engine was simulated numerically to determine the distance influenced by the jet blast from a departing aircraft engine.

“…Benderskiy et al [15], [16] using the RANS/ILES method, have simulated the jet flow of a double-cone supersonic aircraft, detected the influence of co-flow velocity and distance on temperature, pressure fluctuation and axial velocity in the jet hazard area, and studied the influence of natural wind speed on the jet hazard area. Yue et al [17], [18] based on CFD theory and using the standard k-erm equation and three-dimensional n-s equation, have conducted numerical simulation of the jet impact on the flight deck and deflector during the takeoff of the carrier aircraft, and obtained the temperature characteristic distribution on the axis. Song et al [19] have established a simulation model of jet flow of a carrier-borne aircraft, studied the influence of high temperature, high speed and high pressure jet flows on the guide plate under different deflection angles, and compared the simulation results with the experimental results.…”

Section: Introductionmentioning

confidence: 99%

Simulation and Experimental Analysis of the Temperature Field of Jet Flow of Aircraft Based on CFD Theory

Chen

Cai

et al. 2020

IEEE Access

As a key indicator of airport concrete pavement, the durability of concrete is seriously affected by the jet flow generated by aircraft engines. In order to clarify the temperature field distribution of aircraft jet flow acting on the pavement surface, this paper obtained the temperature field distribution of pavement surface under the action of three types of aircraft jet flow by combining field test experiment and CFD simulation. CFD simulation adopts the shear stress transfer model which is often used in engineering problem calculation, and the field test experiment adopts the method of embedding temperature sensor in precast concrete slab. The paired two sample t test was used to test the difference between the experimental results and the simulation results. The experimental results show that the pavement temperature increases first and then decreases with the distance from the engine, and reaches the maximum at the intersection point of the jet flow and the airport pavement. The simulation curve is in good agreement with the experimental results. When the level of confidence is 0.01, there is no significant difference between the simulation value and the experimental value, which verifies the accuracy and feasibility of the simulation calculation model. The simulation results of the three aircraft showed that when type C aircraft is in the state of full afterforce, the maximum pavement temperature is the highest which is 22m away from the nozzle, and can reach 533.81K. The current work provides a new method for measuring the temperature distribution of airfield pavement under the action of jet flow and a basis for the application of fiber concrete in airfield pavement.INDEX TERMS Jet flow, pavement, CFD, test experiment, temperature field distribution.