Wind-tunnel measurements with a fighter aircraft model on a dynamic balance are discussed. The principal fuselage with closed engine inlets was combined with swept back wing, rhombic wing and delta wing and additional horizontal and vertical stabilizer modifications. A strake could be added. The influence of wing shape, stabilizer configuration and strake on the dynamic derivatives of the longitudinal and lateral motion were measured and compared with theoretical computations. Comparison shows that existing theoretical methods can not describe physical phenomena which occur at higher angles of attack.
Flight Mechanics Analysis of Dynamic Derivatives of the Dornier Variable Wind Tunnel Model
1984
124 pages
Report
Keine Angabe
Englisch
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