Balakrishna, S and Niranjana, T and Rajan, SR Moment stability Derivatives of N A G Missile Configuration-at Low Speed using Semi-free Dynamic Flying. Project Report. NAL, Bangalore.
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Abstract
Dynamic flying of scaled model exploits the advantages of flight test methodology and wind tunnel flexibility to generate stability derivative data in evaluated using dynamic flying A 1 : 1 .45 scaled model is flown in a low speed, tunnel and its pitching response to servoed tail drive doublet is analysed using Maximum Likelihood Estimation method . The results indicate a low angle of attack static instability for the tested configuration.
| Item Type: | Proj.Doc/Technical Report (Project Report) |
|---|---|
| Uncontrolled Keywords: | Dynamic Flying;Stability Derivatives |
| Subjects: | AERONAUTICS > Aircraft Design, Testing & Performance |
| Division/Department: | Systems Engineering Division, Systems Engineering Division, Systems Engineering Division |
| Depositing User: | Mr Nisanth |
| Date Deposited: | 17 Jul 2012 10:41 |
| Last Modified: | 17 Jul 2012 10:41 |
| URI: | http://nal-ir.nal.res.in/id/eprint/10582 |
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