Sharma, RC and Gopinath, N and Karthik, N (2009) Concept study of fin mounted tail plane for pitch-up alleviation of LCA. Technical Report. National Aerospace Laboratories, Bangalore, India.
Full text not available from this repository. (Request a copy)Abstract
A new concept for pitch-up alleviation on LCA was investigated. The concept involves introduction of a small swiveling Fin mounted Tail Plane (FTP) mounted above the rudder and through an active control system vary the tail plane angle to mitigate the pitch-up effect. To demonstrate the concept, a simple flat plate delta FTP was designed to fit on to an existing 1:20 scale LCA model and limited wind tunnel tests were carried out. Since simulation of varying FTP angle during wind tunnel tests was not possible, tests were conducted at discrete FTP angles of -5 deg, 0 deg, and 5 deg covering a Mach number range from 0.5 to 1.2 and a beta range of -5 deg. to 5 deg. A few tests were conducted to study the effect of FTP on rudder effectiveness and on lateral characteristics. An assessment of the supersonic drag rise due to FTP was also made at a Mach number of 1.2. Results indicated that a control system operated FTP can successfully mitigate the pitch-up problem at all transonic Mach numbers. The FTP at a fixed angle of 0 deg is found to produce a winglet type of effect and reduced the drag at subsonic and transonic Mach numbers. FTP is found to produce minimal effect on rudder and lateral characteristics. Supersonic drag rise due to FTP is also found to be minimal. While the concept is demonstrated, there is still scope for further improvements in FTP design to obtain better characteristics.
| Item Type: | Monograph (Technical Report) |
|---|---|
| Uncontrolled Keywords: | Pitching moment;Winglets;Delta wing;FTP |
| Subjects: | AERONAUTICS > Aeronautics (General) AERONAUTICS > Aerodynamics |
| Depositing User: | Ms. Alphones Mary |
| Date Deposited: | 28 Jul 2010 08:23 |
| Last Modified: | 28 Jul 2010 08:23 |
| URI: | http://nal-ir.nal.res.in/id/eprint/8836 |
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