i-manager Publications

Aerodynamic Characteristics of Hypersonic Vehicle with Variable Sweep back Wing Configuration

P. Saravanan*, S. Nadaraja Pillai**, K. M. Parammasivam***

* Research Scholar, Department of Aerospace Engg, MIT, Anna University, India.

**Associate Professor, School of Mechanical Engg, S.R.M University, India.

***Assistant Professor, Department of Aerospace Engg, MIT, Anna University, India.

Periodicity:August - October'2009
DOI : https://doi.org/10.26634/jfet.5.1.1018

Abstract

Experimental studies have been conducted to obtain the low speed characteristics of hypersonic vehicle configuration with two different sweep back angle. The vehicle configuration consists of blunt nose, variable sweep back wing, curved fore body Six component force and moment data were obtained over an angle of attack range from —15 to +15 degrees on the 1: 50 scale model in the wind tunnel. The sweep back angles are also changed for different test conditions. The experimental results are presented in terms of lift coefficients Drag coefficients and L/D ratio for various angles of attack and different flow velocities. It is found that there is positive lift coefficient for the configuration at zero angle of attack with considerable drag reduction due to the variable sweepback wings and produces high L/D ratio.

Keywords

CL, CD, Blunt Body, L/D ratio, Angle of Attack, Six Component Strain Gauge Balance.

How to Cite this Article?

Saravanan, P., Pillai, S. N., and Parammasivam, K.M. (2009). Aerodynamic Characteristics Of Hypersonic Vehicle With Variable Sweep Back Wing Configuration. i-manager’s Journal on Future Engineering and Technology, 5(1), 44-50. https://doi.org/10.26634/jfet.5.1.1018

References

[1]. Campell.C and Caram, J NASA Johnson space center, S.Berry,m.D.Fulvio and T.Horvath, NASA Langley research center, “Overview of X-38 hypersonic wind th tunnel data and comparison with numerical results”,35 Aerospace Sciences Meeting & Exhibit, AIAA 97- 0567,January 6-10,1997.

[2]. Donald D.Baala and Edward C.Polhamus, NASA Langley Research Center, “Variable sweep aircraft”, Aerospace Engineering Journal. Vol. 1, No.5,June 1963, pp 12-19

[3].Gnemmi.P,Srulijies,J,Roussel.K and Runne, French- German research Institute of saint-louis,France; “Flow field th around spike tipped bodies”,19 AIAA Applied Aero Dynamics Conference AIAA 2001-2464,11-14 June 2001

[4]. Gregory.J.Brauckmann, NASA Langley Research Center, “X-34 Vehicle Aerodynamic characteristics”, AIAA 98-2531

[5]. Jagadeesh.G,Dhinagaran.R,Haridoaa & Reddy. K.P.J.IISc,I ndia. “Numerical computation of flow and heat transfer around a large angle blunt cone flying at hypersonic Mach number”.

[6]. Kenji oshida,Kenji Hayama,Gifu,Japan “Experimental and numerical study of aerodynamic characteristics for second generation SST”,SAE Journal ,912056, pp 2224 - 2236

[7]. M.R.Mendenhall,H.S.Y.Chou,J.F.Love, Nielson Engineering & Research, “Aerodynamic design and analysis of a reusable launch vehicle”, International council of Aeronautical sciences 2000 congress.

[8]. Mary Mc Wherter Walker and William L.Oberkampf, Sandia. National Laboratories, “Joint Computational / Experimental Aerodynamics Research on a Hypersonic vehicle, Part II: Computational results”, AIAA Journal Vol.30, No.8, August 1992, pp 2009- 2016.

[9]. Pegg.R.J,et al, “Design of a hypersonic waverider derived airplane”, AIAA Paper 93-0401,1993.

[10]. Raman.L. Chase.L.E. Mckinney.M.D. Froning.Jr; “A Two stage to orbit high staging Mach number design concept”, SAE International Journal SAE-2000-01-5605, 2000, pp 1293-1305.

[11]. Robert J.Pegg,David E.Halme and Charles E,Cockrell.Jr NASA Langley Research Centre, Hampton, “Low speed wind tunnel tests of two waverider configuration models” AIAA paper, Sixth International Aerospace planes and Hypersonic Technologies Conference, April 3-7,1995,AIAA 95-6093.

[12]. Report on Tomcat F-14 aircraft (1970).

[13]. Scott D.Holland,William C.woods and Walter C.Engelund, NASA Langley Research Centre, Hampton, “Hyper X research vehicle experimental aerodynamics test programme overview”. Journal of Spacecraft and Rockets, Vol.38, No.6, November-Decmber 2001.

[14]. Viren Menezes, S.Saravanan,G. Jagadeesh,K.P. IISC,Bangalore,“ Aerodynamic drag reduction using aerosipes for large angle blunt cone flying at hypersonic mach number”. 22nd AIAA Aerodynamic measurement technology and ground testing conference, St.Louis, Missouri,AIAA 2702 2709, 24-26 June 2002.

[15].William L.Oberkampf and Danial P.Aeschliman, Sandia National Laboratories, “Joint Computational /Experimental Aerodynamics Research on a Hypersonic vehicle, Part I: Experimental results”, AIAA Journal Vol.30,No.8,August 1992, pp 2000- 2009.

[16]. Yoshito Miyamoto,Toshimi Fujita, Akihiti Iwasaki and Hirotoshi Fujiede, National Aerospace Lab, “Experimental studies on aerodynamic characteristics of SSTO vehicle at low subsonic speeds”,No.911981,SAE Journal ,pp. 2026 2033.

Aerodynamic Characteristics of Hypersonic Vehicle with Variable Sweep back Wing Configuration

Abstract

Keywords

How to Cite this Article?

References

If you have access to this article please login to view the article or kindly login to purchase the article

Purchase Instant Access

Options for accessing this content:

	North Americas,UK, Middle East,Europe		India	Rest of world
	USD	EUR	INR	USD-ROW
Pdf	35	35	200	20
Online	35	35	200	15
Pdf & Online	35	35	400	25