Add to ORKGThe Dynamic Wind Tunnel Simulation Conept Has Been Used\ud To Estimate The Roll Damping Derivatives Of A 1/15 Scale\ud Wind Tunnel Model Of LCA . The Experimental Results Are Compared With Existing Analytical/ Static Wind Tunnel\ud Data For The Same Configuration .\u
As airplane designs have trended toward the expansion of flight envelopes into the high angle of att...
This paper presents the results of a dynamic wind tunnel flying study of the pitching moment coeffic...
Recent progress in the field of Active Controls Technology(ACT) has resulted in increased interest i...
This paper presents the results of estimation of the longitudinal and lateral aerodynamic derivative...
This report gives details of an experimental research investigation carried out in the DSTO water tu...
A method is described for measuring the dynamic stability derivatives of a model airplane in a wind ...
A status report is provided on the collaboration between the Royal Institute of Technology (KTH) in ...
For the experimental determination of dynamic derivatives a new method is presented. Instead of sinu...
Nominal roll control laws were designed, implemented, and tested on an aeroelastically-scaled free-t...
Stabilized Output Error Method (SOEM) Is Applied To LCA-TD1 (SG) Flight Test Data And Aircraft Aerod...
This paper presents a novel method of13; generating comprehensive Longitudinal13; aerodynamic data o...
Stabilized Output Error Method (SOEM) Is Applied To LCA-TD1 (SG) Flight Test Data And Aircraft Aerod...
The control system was developed to control, acquire and process the data from the specially designe...
Aeroelastic Testing Programme of Scaled Aeroelastic model of LCA half wing with rigid fuselage
Pitch Damping Derivatives Were Measured On A 1/12 .5 Scale Prithvi Model Using The Forced Oscillatio...
As airplane designs have trended toward the expansion of flight envelopes into the high angle of att...
This paper presents the results of a dynamic wind tunnel flying study of the pitching moment coeffic...
Recent progress in the field of Active Controls Technology(ACT) has resulted in increased interest i...
This paper presents the results of estimation of the longitudinal and lateral aerodynamic derivative...
This report gives details of an experimental research investigation carried out in the DSTO water tu...
A method is described for measuring the dynamic stability derivatives of a model airplane in a wind ...
A status report is provided on the collaboration between the Royal Institute of Technology (KTH) in ...
For the experimental determination of dynamic derivatives a new method is presented. Instead of sinu...
Nominal roll control laws were designed, implemented, and tested on an aeroelastically-scaled free-t...
Stabilized Output Error Method (SOEM) Is Applied To LCA-TD1 (SG) Flight Test Data And Aircraft Aerod...
This paper presents a novel method of13; generating comprehensive Longitudinal13; aerodynamic data o...
Stabilized Output Error Method (SOEM) Is Applied To LCA-TD1 (SG) Flight Test Data And Aircraft Aerod...
The control system was developed to control, acquire and process the data from the specially designe...
Aeroelastic Testing Programme of Scaled Aeroelastic model of LCA half wing with rigid fuselage
Pitch Damping Derivatives Were Measured On A 1/12 .5 Scale Prithvi Model Using The Forced Oscillatio...
As airplane designs have trended toward the expansion of flight envelopes into the high angle of att...
This paper presents the results of a dynamic wind tunnel flying study of the pitching moment coeffic...
Recent progress in the field of Active Controls Technology(ACT) has resulted in increased interest i...