Wing Planform Design Optimization for Reusable Launch Vehicle

Manokaran, K.; Vidya, Gayatri; Sivaramakrishnan, A. E.; Goyal, Virendra Kumar

doi:10.2514/1.39732

Cited by 3 publications

(2 citation statements)

References 1 publication

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“…Polynomial regression metamodels have been implemented in a wide range of aerodynamic applications including helicopter rotor blades [4], launch vehicle wing [5], NASA rotor67 [6], high-speed civil transport [7], flying wings [8], transonic airfoils [9], and predicting the aerodynamic coefficients of cranked wings [10].…”

Section: Figure 1 a Typical Flow Pattern Around A Symmetric Diamond-mentioning

confidence: 99%

Surrogate Representation for the Aerodynamic Coefficients of Supersonic Airfoils

Ahmed¹

2015

International Conference on Aerospace Sciences and Aviation Tec

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Generally, physical phenomena are represented in the form of explicit mathematical expressions that stem from basic governing equations. However, in many cases, having these expressions may not be achieved and a considerable part of our knowledge relies on abstract numbers produced via lab experiments or computer simulations. In the absence of explicit relations for the variables of the physical phenomena, surrogates emerge as a reliable alternative. Surrogates have evolved in the recent years and gained the attention of researchers and, in the field of aerodynamics; surrogates have been widely used in multiple applications. In the present paper, surrogates are implemented in a new application namely, the relation between the design of a 10% diamond airfoil and its aerodynamic coefficients. Kriging interpolation and polynomial regression surrogates are constructed based on data taken from CFD simulations of the turbulent, Mach 2, zero-incidence flow about 104 airfoil samples representing almost all possible designs of that airfoil. The constructed surrogates are proved to incorporate the CFD data with a high accuracy. They also yield useful visual representations of the physical phenomena in hand and generate simple mathematical expressions for these phenomena as well.

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Section: Figure 1 a Typical Flow Pattern Around A Symmetric Diamond-mentioning

confidence: 99%

Surrogate Representation for the Aerodynamic Coefficients of Supersonic Airfoils

Ahmed¹

2015

International Conference on Aerospace Sciences and Aviation Tec

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“…A fully reusable vertical-takeoff-andvertical-landing (VTVL) rocket [1] is considered capable of achieving these goals, and a significant amount of research focusing on this rocket has been conducted at the Institute of Space and Astronautical Science/Japan Aerospace Exploration Agency (ISAS/JAXA). So far, many types of reusable rockets have been proposed and studied globally [1][2][3][4][5], and each type has its advantages and disadvantages. However, VTVL type has a significant advantage over other types such as horizontal-takeoff-and-horizontal-landing (HTHL) type, as a VTVL rocket needs neither large wings nor runways, since it is launched by a rocket engine -this enables us to save significant cost.…”

Section: Introductionmentioning

confidence: 99%

High Angle-of-Attack Pitching Moment Characteristics of Slender-Bodied Reusable Rocket

Aogaki

Kitamura

Nonaka

2018

Journal of Spacecraft and Rockets

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The development of a fully reusable vertical-takeoff-and-vertical-landing (VTVL) rocket is indispensable for reducing space transportation costs. However, there are many technical issues associated with such vehicles, such as the safe execution of a turnover maneuver during return flight. It is known that a relatively desirable pitching moment characteristic for turnover can be accomplished by employing a slender body configuration, but the reason for this is not well understood. In this study, we carried out a delayed detached-eddy simulation (DDES) on the aerodynamic characteristics of such a slender-bodied reusable rocket for angles of attack between 0 and 180 degrees using unstructured compressible computationalfluid-dynamics (CFD). We also conducted inviscid calculations in order to distinguish the pitching moment contribution of the body configuration itself from the effects of viscosity and turbulence. It was found that two types of vortices were formed at 0-90 degrees, and also these vortices affected the pitching moment distribution. We also observed three types of vortices generated at 90-180 degrees. Combined with the results of the inviscid simulation, we concluded that the pitching moment characteristic is greatly impacted by the behaviors of these vortices and bubbles.

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Dynamic Programming

2015

Optimization

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Wing Planform Design Optimization for Reusable Launch Vehicle

Cited by 3 publications

References 1 publication

Surrogate Representation for the Aerodynamic Coefficients of Supersonic Airfoils

Surrogate Representation for the Aerodynamic Coefficients of Supersonic Airfoils

High Angle-of-Attack Pitching Moment Characteristics of Slender-Bodied Reusable Rocket

Dynamic Programming

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