Bio: P Theerthamalai is an academic researcher from Defence Research and Development Laboratory. The author has contributed to research in topics: Pitching moment & Fineness ratio. The author has an hindex of 1, co-authored 1 publications receiving 1 citations.
09 Jan 2006
TL;DR: In this article, the applicability of PARAS-3D for the prediction of the external aerodynamics of body-intake configurations and also to find the effect of flow through intakes on external aerodynamic coefficients.
Abstract: Aerodynamic study over body-intake configurations has been carried out using a CFD code, PARAS. Body -Twin Intake and Body-Cruciform Intake configurations were studied. The air- intakes are two-dimensional. Computations were carried out for Mach numbers 2.0 and 3.0, angle of incidence from -10 o to +10 o and roll angles 0 o and 45 o . Computations with and without flow through the intakes were carried out. The CFD results were compared with the experimental data and the agreement is found to be good. The effect of flow through intakes on normal force and pitching moment is not significant where the effect is significant on axial force. 6 and Vipin kumar 7 on body-intake configurations for measurement of external aerodynamic coefficients. The objective of present study is to find the applicability of the CFD code, PARAS-3D for the prediction of the external aerodynamics of body-intake configurations and also to find the effect of flow through intakes on external aerodynamic coefficients. The details of body-intake configurations, PARAS-3D code and the computational results are presented. Comparison of the CFD results with experimental data is also presented. II. Body-intake Configurations Two configurations were investigated. configuration-1 consists of body with two side-mounted intakes (twin intake configuration) and configuration-2 consists of body with four intakes (cruciform intake configuration). The body consists of ogival nose followed by circular cylinder. The body is identical for both configurations. Diameter of the body is 27 mm. Nose fineness ratio is 3 and slenderness ratio of the model is 15. The intakes are 2-dimensional. Length and span of intakes of both configurations is same. Thickness of intakes of twin intake configuration is twice that of intakes of cruciform configuration. For twin intake configuration, intake entry plane is not facing the body. For cruciform intake configuration, intake entry plane is facing the body. Angle of intake entry plane is 34.4° with respect to flow direction for all he intakes. The details of the configurations are shown in Fig.1. In the flow through condition, the thickness of the intake walls is taken as 0.5mm. III. PARAS-3D code PARAS-3D code is a PARallel Aerodynamic Simulator, which can simulate viscous, turbulent and three-dimensional fluid flow over arbitrary three-dimensional bodies. The grid around the bodies is generated by means of a Rectangular Adaptive Cartesian Mesh (RAM) technique. This code is based on explicit scheme with second order accurate in space and of total variation diminishing (TVD) type, which is $
TL;DR: Wang et al. as mentioned in this paper proposed an integrated design method for the inlet and the missile body with two side layout under asymmetric inflow, and the result of numerical simulation shows that shock waves hit on cowl lip on the symmetry plane at the design condition.
Abstract: Abstract Based on the flow field characteristics of the missile body, an integrated design method for missile and inlet with two side layout is proposed under asymmetric inflow. The result of numerical simulation shows that shock waves hit on cowl lip on the symmetry plane at the design condition, which verifies the method of integrated design. And the flow characteristics of inlet under the influence of the missile body are analyzed. Under the influence of asymmetric incoming flow and missile body, the first shock wave surface of the two-dimensional inlet presents the characteristics of a three-dimensional concave surface, and there is a pair of asymmetric vortex structures in the inner flow path. Finally, a bleed cavity of self-adaptively adjusting bleeding by vortex is proposed to improve the performance of inlet and broaden the inlet start and attack angle boundary. The minimum Mach number of the inlet start is reduced from 2.8 to 2.3 at ɑ = 6° and the maximum attack angle of inlet start is widened from ɑ = −1° to ɑ = 3° at Ma = 2.1.