Experimental Studies on 1/15th Scale SARAS Afterbody Model with Underside Fuselage Fairing, Ventral Fins, Nacelles and Stub Main Wing.

Mathur, NB and Rajeev, Kumar (2004) Experimental Studies on 1/15th Scale SARAS Afterbody Model with Underside Fuselage Fairing, Ventral Fins, Nacelles and Stub Main Wing. Technical Report. National Aerospace Laboratories, Bangalore, India.

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Abstract

Results presented here are from a experimental study conducted on a 1-15th scale SARAS upswept fuselage afterbody model designed with underside fuselage fairing, ventral fins, nacelles and stub main wing to assess total drag characteristics and certain broad flow features of this afterbody configuration. Experiments where carefully designed and conducted in a special purpose 0.5m base flow wind tunnel, exploiting unique features of this facility for these experimental studies, generally difficult to carry out in a conventional wind tunnel facility. Afterbody total drag measurements (as well as the contribution of each of the afterbody components i-e. ventral fins etc), surface pressure measurements (longitudinal as well as circumferential) and surface flow visualization studies have been carried out in the freestream Mach number range of 0.40 to 0.70. Test results show that the nacelles contribute a significant amount (about 80-84%) to the total afterbody drag. The typical value of the total afterbody drag at M-=0.50 is 0.0122 (based on wing planfon area). Surface flow visualization studies and afterbody surface pressure distributions reveal effect of primary vortex formed as a result of cross flow separation.

Item Type: Monograph (Technical Report)
Uncontrolled Keywords: Base flow tunnel;SARAS;Fugelage afterbody;Flow visualization; Under-fuselage fairing;Ventral-fins;Nacelle;Cross flow separation;Total drag
Subjects: AERONAUTICS > Aeronautics (General)
AERONAUTICS > Aerodynamics
Depositing User: Users 11 not found.
Date Deposited: 18 Nov 2011 11:10
Last Modified: 18 Nov 2011 11:10
URI: http://nal-ir.nal.res.in/id/eprint/10091

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