Experimental Study on Pitch up Problem Associated with Compound Delta Wings of Combat Aircraft Configurations

Sajeer, Ahmed and Sudhakar, S (2010) Experimental Study on Pitch up Problem Associated with Compound Delta Wings of Combat Aircraft Configurations. Project Report. National Aerospace Laboratories, Bangalore.

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Experiments were carried out on two compound delta wing configuration with first sweep angle of 50°& 55° and a second sweep of 60° in the 0.3m Trisonic wind tunnel for a Mach number range of 0.5 to 0.85 in the angle of incidence range 0° to 20°. Data was also generated for a baseline delta wing configuration with sweep angle of 60°. The results were analyzed to understand the effect of variation in first sweep and Mach number for the existence of pitch up. Oil flow visualization has been carried out for the limited case to infer the flow field associated with the pitch up. Analysis of the aerodynamic data showed the presence of pitch up in all the three configuration tested. Decrease in first sweep has shown an increase in the magnitudes of the pitching moment and occurrence of pitch up shifting to lower incidence angles. Increase in Mach number has shown similar variation and no pitch up was observed at Mach number of 0.85 for the configuration having compound sweep of 50°/60°. Surface flow patterns supplements the force data and indicates the flow pattern over the wing is affected by first sweep and is predominantly dominated by a vortex from the first sweep and considerable difference in flow pattern is observed over the area covered by the first sweep compared to single 60° delta configuration.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: Compound delta wing, Pitch up, Subsonic speeds
Subjects: AERONAUTICS > Aerodynamics
Depositing User: Smt Bhagya Rekha KA
Date Deposited: 15 Nov 2011 04:38
Last Modified: 15 Nov 2011 04:38
URI: http://nal-ir.nal.res.in/id/eprint/9984

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