© 2018 JETIR March 2018, Volume 5, Issue 3 www.jetir.org (ISSN-2349-5162) JETIR1803081 Journal of Emerging Technologies and Innovative Research (JETIR) www.jetir.org 425 NUMERICAL ENHANCEMENT OF HEAT TRANSFER OF FIN AND TUBE COMPACT HEAT EXCHANGER USED IN AEROSPACE USING CFD AnuragChoubey, Prof. D.S. Rawat 2 M.Tech scholar 1 , Assistant Prof. Mechanical department 2 Jabalpur Engineering College, Jabalpur Abstract  In the present study, the hydrodynamic and heat transfer characteristics of compact fin andtube heat exchangers have been investigated numerically. The aim is to analyze the influence of operating conditions and the geometry parameters of compact heat exchanger to design more efficient heat transfer device. Fin spacing and fin thickness are the geometrical parameters.The over-fin fluid velocity or Reynolds number is used as the parameter of operation. Here in this work it finds the effect of different material, fin thickness and fin spacing on heat transfer enhancement of the compact heat exchanger. Here in this work four different Reynolds number that is 2622.96, 5248.98, 7873.25 and 10497.96 were considered to analyze the effect of different velocity of fluid. It also analyzed the effect of different materials used for the construction of Fin and tube, in this work three different steel alloys that is GH2132, GH3044 and S66280 were considered for the analysis in which GH3044 shows the better heat transfer as compared to other.For GH3044 material heat transfer rateis 15 % more than the GH2132 material. Whereas domain having 0.8 mm fin spacing shows 5 % increase in heat transfer as compared to 1.1 mm fin spacing. 1. Introduction The speed of aircraft has increased from subsonic to supersonic over the last decades because of the advent and development of the aircraft jet engine. Recently, the technologic research on the aerospace plane made a higher demand of speed (up to 5 Mach) and as the result, the engine for hypersonic aircraft become a challenge of 21st century. As modern gas turbine used in aero engines, to achieve higher thermal efficiency, the inlet temperature of turbine increases and increasing pressure ratio inside the compressor are most commonly used methods. With the development of engine technology, current turbine inlet temperature is far beyond the allowable metal temperatures range, which is approaching near about 2000 K. As the material properties development lagged behind the demand of practical application, turbine inlet temperature increased further by using highly sophisticated cooling techniques. Fin-tube compact heat exchangers show potential applications in aero engines for their high efficiency. As compared with the traditional heat exchangers used on the ground, those used in aero engines are more compact and suffer higher temperatures and larger temperature differences. The temperature change over the exchanger depth and the temperature gradient in the near wall region are more conspicuous, they may reach several hundred degrees.