Characteristics of Base Drag and Flow with Nozzle Flow Conditions in Supersonic Flow

Nam, Junyeop; Kim, Duk-Min; Roh, Tae‐Seong; Lee, Hyoung Jin

doi:10.1007/s42405-022-00513-z

Cited by 2 publications

(8 citation statements)

References 19 publications

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“…Therefore, it is considered reasonable to obtain results via 2D axisymmetric simulation. The numerical techniques utilized in this study were validated in a previous study [25]. A two-dimensional axisymmetric steady-state RANS equation and density-based coupled solver were applied as follows:…”

Section: Numerical Approachmentioning

confidence: 99%

“…The RANS method is widely used in aerospace studies, and sufficient validation was performed to ensure the reliability of the numerical method used in this study. The turbulence model was a realizable k-ε model, which was selected via validation [25]. The k-ε turbulence model solves transport equations for the turbulent kinetic energy k and the turbulent dissipation rate ε, and the realizable k-ε model contains a new transport equation for the turbulent dissipation rate.…”

Section: Numerical Approachmentioning

confidence: 99%

“…Several experiments and numerical simulations have been performed to predict base drag. Such studies have been conducted for subsonic [1][2][3], transonic [4][5][6][7][8][9], and supersonic [10][11][12][13][14][15][16][17][18][19][20][21][22][23][24][25][26][27] flow. Because the current study focuses on supersonic flows, only those on supersonic flows are discussed herein.…”

Section: Introductionmentioning

confidence: 99%

“…Because the current study focuses on supersonic flows, only those on supersonic flows are discussed herein. Previous studies can be divided into wind tunnel studies [10][11][12][13][14][15][16][17][18] and numerical simulations [19][20][21][22][23][24][25][26][27][28][29][30][31][32][33][34][35]. Wind tunnel studies with cold flow were conducted to create base pressure data for the combustion chamber pressure in supersonic flow [10,11].…”

Section: Introductionmentioning

confidence: 99%

“…Some studies investigated the base pressure according to the base and nozzle configurations in supersonic flow [19][20][21][22]. The base drag of the aircraft body according to the on/off power of the thrust has been reported [23][24][25][26]. Additionally, hot gas flow experiments and numerical simulations have been conducted.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Base Flow and Drag Characteristics of a Supersonic Vehicle with Cold and Hot Jet Flows of Nozzles

Kim,

Nam,

Roh

et al. 2023

Aerospace

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Base drag has a significant effect on the overall drag of a projectile in a supersonic flow. Herein, the base drag and flow characteristics of cold and hot gas flow in a supersonic flow are analyzed via numerical simulations. The hot gas flow is simulated using a chemical equilibrium application code based on hydrogen combustion. Two types of nozzle configurations, namely conical and contoured, are chosen for the simulation. The simulation results reveal that the change in base drag is 5–85% according to the injection gases. In the over-expanded and slightly under-expanded conditions, the base drag decreases in the hot gas flow, owing to the weak expansion fan caused by the high-temperature nozzle flow expansion, whereas in the highly under-expanded condition, the base drag decreases, owing to the strong shock wave near the base caused by the deflection of the recirculation region toward the body wall. In addition, the variations in base flow structures are observed differently compared with the cold flow; for example, a weak oblique shock wave at the nozzle exit, an increase in the distance between the shock wave and base, and deflection of the recirculation region based on the body wall are observed.

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Section: Numerical Approachmentioning

confidence: 99%

Section: Numerical Approachmentioning

confidence: 99%