A new method for calculating surface pressures on bodies at an angle of attack in supersonic flow

Dejarnette, Fred R.; Ford, CW Pitt; Young, Dana

doi:10.2514/6.1979-1552

Cited by 6 publications

(2 citation statements)

References 4 publications

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“…The method calculates the zero incidence surface pressure on the isolated fuselage, and off-surface velocity and pressure field around it. The effect of angle of attack on both the surface pressure and the flow field is calculated using the slender body theory based method of de Jarnette [6]. The increment in the inflow Mach number along the span of the wing is then calculated and applied to the VFP solution of the wing flow, thereby resolving the influence of the fuselage on wing.…”

Section: B the Vfp Solvermentioning

confidence: 99%

Progress towards a Rapid Method for Conceptual Aerodynamic Design for Transonic Cruise

Prince

Pasquale

Garry

2020

AIAA Scitech 2020 Forum

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Results are presented from a study aimed at demonstrating the accuracy and efficiency of a lower order aerodynamic prediction method for transonic cruise flows around aircraft configurations, including conventional swept wing-body and also blended wing-body designs. The Viscous Full Potential (VFP) method, coupling the solution of the full potential equations with the integral boundary layer equations can yield data of almost equivalent accuracy as Navier-Stokes based CFD methods but at 0.5%-2% of the physical time. In addition it is shown, using both the VFP approach and Delayed Detached Eddy Simulation (DDES) that the flow physics of the stall mechanism associated with blended wing-body configurations is far more complex than that experienced on more conventional swept-tapered wings. The mechanism appears to involve an initial tip stall but also involves highly 3D vortical flows inboard on the upper surface of the wing which significantly distorts the transonic shock wave.

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Section: B the Vfp Solvermentioning

confidence: 99%

Progress towards a Rapid Method for Conceptual Aerodynamic Design for Transonic Cruise

Prince

Pasquale

Garry

2020

AIAA Scitech 2020 Forum

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“…The first of these was to give an improved pressure coefficient prediction on the blunt nose of a missile configuration over that provided by the MNT. If the pressure coefficient of MNT is defined as (Cp)wr = Cpsin 26 eq (67) then the nose pressure on the blunt nose part of a missile is given by CP Cp).…”

Section: T= T(ps) P = P(ps) (65) a = A (P S) E = E(p S)mentioning

confidence: 99%

State-of-the-Art Engineering Aeroprediction Methods with Emphasis on New Semiempirical Techniques for Predicting Nonlinear Aerodynamics on Complete Missile Configurations

Moore¹

1993

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Evaluation of reduced-order models for the rapid aerodynamic analysis of supersonic and hypersonic bodies

Urraza Atue,

Bruce

2024

Aeronaut. j.

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This paper presents a comprehensive evaluation of reduced-order models (ROMs) for the determination of pressure coefficient distributions on supersonic and hypersonic bodies. The study investigates the limitations, aerodynamic precision and computational performance associated with various methodologies, ranging from simplistic Newtonian theory-based approaches to more advanced first and second-order shock-expansion theories. Validation is performed by comparing computed results with experimental and computational data for pressure distributions, drag and lift coefficients and centres of pressure for fundamental geometries and authentic vehicle design over a wide range of freestream conditions. The study also includes a comprehensive computational complexity analysis, demonstrating the superiority of finite-element ROM approaches over traditional finite-volume computational fluid dynamics (CFD) simulations. The primary objective of this paper is to scrutinise the extension of these methodological classes to the low supersonic regime. Hence, thermo-chemical reactions within the flow are disregarded, and the ideal gas law is adopted. A value of $\gamma = 1.4$ is chosen for consistency and comparability across the analyses. The proposed ROMs show remarkable potential for reducing high-speed simulation execution times by four orders of magnitude, maintaining accuracy within 20 per cent and as low as 1 per cent. The study unveils three key findings: first, the accuracy degradation of Newtonian-based theories for inclined elements, particularly around 45 degrees, and their reduced dependency on Mach number at large inclination. Secondly, the study presents novel insights into the impact of shock-wave-Mach-wave interactions on pressure distribution calculations, emphasising the Mach number as a crucial metric governing recompression effects. Lastly, the study demonstrates the exceptional accuracy of DeJarnette’s method, providing ${C_P}$ results within 2 per cent for a wide range of conditions, offering an attractive alternative to the Taylor-Maccoll equation.

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A new method for calculating surface pressures on bodies at an angle of attack in supersonic flow

Cited by 6 publications

References 4 publications

Progress towards a Rapid Method for Conceptual Aerodynamic Design for Transonic Cruise

Progress towards a Rapid Method for Conceptual Aerodynamic Design for Transonic Cruise

State-of-the-Art Engineering Aeroprediction Methods with Emphasis on New Semiempirical Techniques for Predicting Nonlinear Aerodynamics on Complete Missile Configurations

Evaluation of reduced-order models for the rapid aerodynamic analysis of supersonic and hypersonic bodies

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