Experimental Studies on 1/15th Scale SARAS Afterbody Model with Underside Fuselage Fairing, Ventral Fins, Nacelles and Stub Main Wing.
IR@NAL: CSIR-National Aerospace Laboratories, Bangalore
View Archive Info| Field | Value | |
| Title |
Experimental Studies on 1/15th Scale SARAS Afterbody Model with Underside Fuselage Fairing, Ventral Fins, Nacelles and Stub Main Wing.
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| Creator |
Mathur, NB
Rajeev, Kumar |
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| Subject |
Aeronautics (General)
Aerodynamics |
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| Description |
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.
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| Publisher |
National Aerospace Laboratories
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| Date |
2004-03
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| Type |
Proj.Doc/Technical Report
NonPeerReviewed |
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| Format |
application/pdf
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| Identifier |
http://nal-ir.nal.res.in/10091/1/Experimental_Studies.pdf
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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| Relation |
http://nal-ir.nal.res.in/10091/
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