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Abstract
In this study, a numerical investigation was conducted on the nozzle outlet flow of vertical takeoff and landing aircraft. The flow was assumed to be steady and incompressible, and the governing equations were discretized and solved using FLUENT commercial software. The aircraft's outlet jets were modeled as both rectangular and circular cross sections. Variations in pressure, particularly dynamic pressure, from the centroid of the nozzle outlet to the ground level were plotted. The findings demonstrated good agreement with available experimental data, emphasizing that dynamic pressure decreases as the ground vicinity is approached.
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References
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References
Martin, https://en.wikipedia.org/wiki/Lockheed_Martin_F-35_Lightning-II (Accessed on April 14th ,2017)
F. P. Ricou, D. B. Spalding. (1961). Measurements of entrainment by axisymmetric turbulent jets. J Fluid Mech, 11 (1), pp 21–32.
P. O. Witze. Centerline velocity decay of compressible free jets. AIAA J, 12 (4) (1974), pp 417–418.
J. G. Gentry, R. Margason. (1966).Jet-induced lift losses on VTOL configurations hovering in and out of ground effect. Technical Note D- 3166, NASA.
P. Shumpert, J. Tibbetts. (1969). Model tests of jet-induced lift effects on a VTOL aircraft in hover. Contractor Report 1297, NASA.
J. Williams, M. Wood. (1996).Aerodynamic interference effects with jet-lift V/STOL aircraft under static and forward speed Conditions. Technical Report 66403, RAE.
J. David. (2008).Aerodynamic modeling of jet-lift V/STOL aircraft under static conditions", Conference Paper, Singapore, IEEE.
Naimzad, Arif. (2017). ANSYS applications [Practical Experiment in the Lab], Kabul University.
Naimzad, Arif. (2017). Origin Pro applications [Data Analysis in the Lab], Kabul University.
Naimzad, Arif. (2018). FLUENT applications [Practical Experiment in the Lab], Kabul University.