Pashilkar, AA (2001) Flow incidence rate model for unsteady aerodynamics at high angles of attack AIAA Paper 2001-2469. In: 19th Applied Aerodynamics Conference, 11-14 June 2001, Anaheim, CA.
![[img]](https://nal-ir.nal.res.in/style/images/fileicons/application_pdf.png) |
PDF
2001-2469.PDF Restricted to Registered users only Download (890kB) |
Abstract
A new modeling structure is proposed for the unsteady variation of aerodynamic coefficients of a delta wing aircraft. The model is based on suitable modulation of the static data with lagged incidence rate. The novel modeling structure is shown to be consistent with the static, small amplitude forced oscillations and the large amplitude sinusoidal response characteristics of a delta wing wind tunnel model with a sweep angle close to 60 degrees. 13; 13;
| Item Type: | Conference or Workshop Item (Paper) |
|---|---|
| Additional Information: | AIAA 2001-2469 |
| Uncontrolled Keywords: | Unsteady Aerodynamics;Angle Of Attack;Delta Wings;Wind Tunnel Models;Sweep Anglefighter Aircraftmathematical Modelincidenceaerodynamic Denceaerodynamic Stalling |
| Subjects: | AERONAUTICS > Aeronautics (General) |
| Depositing User: | Mr. N A |
| Date Deposited: | 27 Jan 2006 |
| Last Modified: | 27 Aug 2015 06:04 |
| URI: | http://nal-ir.nal.res.in/id/eprint/1000 |
Actions (login required)
 |
View Item |
