Development of Dynamic Stability Derivatives of an Airplane from Static Wind Tunnel Tests

2004 ◽  
Author(s):  
Byeong-Hee Chang ◽  
Sang-Oh Cho ◽  
Tae-Hwan Cho ◽  
Ki-Chul Lim ◽  
Sung Hwan Hwang
Keyword(s):  
Wind Tunnel ◽  
Dynamic Stability ◽  
Wind Tunnel Tests ◽  
Stability Derivatives ◽  
Derivatives Of

Aerodynamics analysis of the main rotor influence on the static stability of the gyroplane

2017 ◽  
Vol 89 (5) ◽  
pp. 663-670 ◽  
Author(s):  
Marcin Figat
Keyword(s):  
Dynamic Stability ◽  
Static Stability ◽  
Main Rotor ◽  
Aerodynamic Coefficients ◽  
Content Type ◽  
Flight Condition ◽  
Configuration Change ◽  
Stability Derivatives ◽  
The Impact ◽  
Derivatives Of

Purpose This paper aims to present the results of aerodynamic calculation of impact the main rotor on the fuselage and the tail of a light gyroplane. This kind of vehicle is a type of rotorcraft which uses a non-powered rotor in autorotation to develop lift and engine-powered propeller to provide the thrust. Both of them disturb the flow around the gyroplane body (gyroplane fuselage and tail) and influence on its static stability. The main goal of the presented research was to find the magnitude of this influence. To measure this effect, the main stability derivatives changes of gyroplane body were investigated. Design/methodology/approach The CFD analysis of the complete gyroplane was made. Computation was performed for the model of gyroplane which was equipped with the two sub-models of the main rotor and the engine-powered propeller. Both of them were modelled as the actuator discs. This method allows to compute the aerodynamic impact of rotating components on the gyroplane body. All aerodynamic analysis was made by the MGAERO software. The numerical code of the software bases on the Euler flow model. Next, the resulting aerodynamic coefficients were used to calculate the most important stability derivatives of the gyroplane body. Findings The result obtained by computation presents the change in the most important aerodynamic coefficients and stability derivatives of the gyroplane body caused by the impact of its main rotor. Moreover, the result includes the change of the aerodynamic coefficients and stability derivatives caused by change of the main rotor configuration (change of rotation rate and angle of incidence) and change of the flight condition (gyroplane angle of attack sideslip angle and flight speed). Practical implications Analysis of the main rotor impact will be very useful for evaluation of dynamic stability of the light gyroplane. Moreover, the results will be helpful to design the horizontal and vertical tail for the light gyroplane. Originality/value This paper presents the method of the numerical analysis of the static stability of the light gyroplane’s body. The results of analysis present the impact of disturbance generated by the rotating main rotor on the static stability of the gyroplane body. Moreover, the impact of the main rotor configuration change and the flight condition change on the static stability were investigated too. The evaluation of the gyroplane’s body static stability was made by the stability derivatives. The methodology and obtained result will be very useful for analysis of the dynamic stability of the light gyroplanes. Moreover, the results will be helpful during design the main components of the gyroplane like vertical and horizontal tail.

DETERMINATION OF FLUTTER DERIVATIVES OF BRIDGE DECKS BY COVARIANCE-DRIVEN STOCHASTIC SUBSPACE IDENTIFICATION

2011 ◽  
Vol 11 (01) ◽  
pp. 73-99 ◽  
Author(s):  
THARACH JANESUPASAEREE ◽  
VIROTE BOONYAPINYO
Keyword(s):  
Wind Tunnel ◽  
Thin Plate ◽  
Bridge Deck ◽  
Bridge Decks ◽  
Subspace Identification ◽  
Plate Model ◽  
Wind Tunnel Tests ◽  
Stochastic Subspace Identification ◽  
Derivatives Of ◽  
Flutter Derivatives

In this paper, the covariance-driven stochastic subspace identification technique (SSI-COV) was presented to extract the flutter derivatives of bridge decks from the buffeting test results. An advantage of this method is that it considers the buffeting forces and responses as inputs rather than as noises. Numerical simulations and wind tunnel tests of a streamlined thin plate model conducted under smooth flows by the free decay and the buffeting tests were used to validate the applicability of the SSI-COV method. Then, the wind tunnel tests of a two-edge girder blunt type of industrial-ring-road (IRR) bridge deck were conducted under smooth and turbulence flows. The flutter derivatives of the thin plate model identified by the SSI-COV technique agree well with those obtained theoretically. The results obtained for the thin plate and the IRR bridge deck are used to validate the reliability and applicability of the SSI-COV technique to various wind tunnel tests and conditions of wind flows. The results also show that for the blunt-type IRR bridge deck, the turbulence wind will delay the onset of flutter, compared with the smooth wind.

Dynamic stability wind-tunnel tests of a 10 deg cone with simulated ablation at m equals 17.

AIAA Journal ◽  
1967 ◽  
Vol 5 (8) ◽  
pp. 1377-1385 ◽  
Author(s):  
D. R. MOORE ◽  
C. J. STALMACH ◽  
T. C. POPE ◽  
J. E. JENKINS
Keyword(s):  
Wind Tunnel ◽  
Dynamic Stability ◽  
Wind Tunnel Tests
Sign in / Sign up

Export Citation Format

Share Document