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Please use this identifier to cite or link to this item: https://gnanaganga.inflibnet.ac.in:8443/jspui/handle/123456789/7069
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dc.contributor.authorAmit Kumar-
dc.contributor.authorVinay Yadav-
dc.date.accessioned2024-02-27T06:05:35Z-
dc.date.available2024-02-27T06:05:35Z-
dc.date.issued2015-
dc.identifier.urihttp://gnanaganga.inflibnet.ac.in:8080/jspui/handle/123456789/7069-
dc.description.abstractThis paper brings us the aero dynamics properties of flow over symmetrical aerofoil (NACA-0012) at low subsonic speed (M<0. 3). Generally symmetrical aerofoil are used in supersonic aircraft for military purpose like fighter and bomber to give smooth speed at supersonic speed (M> 1) and including compressible effect. Here attempt has been made to determine pressure distribution over symmetrical aerofoil at low sub-sonic speed and in viscid incompressible flow. The flow behavior on symmetrical aerofoil of upper and lower side has been investigated.-
dc.publisherAnusandhan- AISECT University Journal-
dc.titleExperimental View on Performance of Flow Past Over a Symmetrical Aerofoil at Low Subsonic Speed-
dc.volVol 4-
dc.issuedNo 7-
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