Supersonic Flow Fields with Various Deceleration Levels

Yamashita, Yuya; Fujiwara, Hajime; Suzuki, Takayoshi; Iwakawa, Akira; Sasoh, Akihiro; Mahomed, I.; Roohani, H.; Gledhill, Irvy Ma; Skews, B. W.

doi:10.3850/978-981-11-2730-4_0496-cd

Cited by 2 publications

(3 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…There was excellent agreement in the bow-shock standoff distance between simulation using The experimental validation for the MRF acceleration technique is shown in Fig. 5 based on the free-flight ballistic range experiment by Yamashita et al [3]. This experiment used a hollow hemispherecylinder-flare-cylinder, with a 6.5 slenderness ratio and 6mm effective diameter.…”

Section: Unsteadymentioning

confidence: 89%

“…The ballistic range experiments provide insight into unsteady shock wave motion during deceleration with approximately straight and level flight. A few suitable cases are reported in the literature for the transonic and supersonic regime [1,2,3].…”

Section: Introductionmentioning

confidence: 99%

“…More recently, ballistic range experiments by Yamashita et al [3] investigated the separation shock angle with boundary layer interaction for a hemisphere-cylinder-flare-cylinder projectile with Mach numbers of approximately 2.0. They showed that the separation shock angle decreased with increasing deceleration magnitudes, in the range of 800 to 1 600g.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Unsteady shock wave dynamics in accelerating and decelerating flight

et al. 2021

Self Cite

View full text Add to dashboard Cite

Increasingly agile manoeuvre is an advantage in the flight of aircraft, missiles and aerial vehicles, but the principles of accelerating aerodynamics in the transonic regime are only now being fully investigated. This study contributes to the understanding of shock and separation effects on drag during axial acceleration, using a simple geometric configuration. Unsteady shock wave behavior was numerically investigated for an axisymmetric cone-cylinder using a commercial solver and the Moving Reference Frame acceleration technique. This acceleration technique was validated using unsteady numerical and experimental methods. The cone-cylinder was accelerated from Mach number 0.6 to Mach number 1.2 at 100g constant and deceleration was from Mach number 1.2 until Mach number 0.6 at –100g constant. Three cone angles were tested for the cone-cylinder with uniform cylinder diameter. Acceleration through the transonic Mach regime was characterised by a delayed and gradual shock wave development when compared to steady state, demonstrating a clear flow history effect. Deceleration through the transonic Mach regime was characterised by shock wave propagation from the base to the nose. New flow structures appeared during deceleration that do not have counterparts in the steady state, including shock interactions and propagating expansion-compression features. Gross changes in the unsteady drag coefficient curves for each cone-angle are explained with reference to unsteady shock wave behaviour for accelerating and decelerating motion.

show abstract

Section: Unsteadymentioning

confidence: 89%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation