A Method of Determining Some Aerodynamic Coefficients from Supersonic Free-Flight Tests of a Rolling Missile

1950 ◽  
Vol 17 (10) ◽  
pp. 609-621 ◽  
Author(s):  
RAY E. BOLZ ◽  
JOHN D. NICOLAIDES
Keyword(s):  
Free Flight ◽  
Aerodynamic Coefficients ◽  
Flight Tests

Identifiability investigation of the aerodynamic coefficients from free flight tests

2013 ◽  
Author(s):  
Marie Albisser ◽  
Simona Dobre ◽  
Claude Berner ◽  
Magalie Thomassin ◽  
Hugues Garnier
Keyword(s):  
Free Flight ◽  
Aerodynamic Coefficients ◽  
Flight Tests

scholarly journals Aerodynamics of inclined cylindrical bodies free-flying in a hypersonic flowfield

2021 ◽  
Vol 62 (9) ◽  
Author(s):  
Patrick M. Seltner ◽  
Sebastian Willems ◽  
Ali Gülhan ◽  
Eric C. Stern ◽  
Joseph M. Brock ◽  
...  
Keyword(s):  
High Speed ◽  
Degrees Of Freedom ◽  
Numerical Data ◽  
Static Stability ◽  
Free Flight ◽  
Aerodynamic Coefficients ◽  
Flow Topology ◽  
Motion Data ◽  
Continuous Rotation ◽  
German Aerospace

Abstract The influence of the flight attitude on aerodynamic coefficients and static stability of cylindrical bodies in hypersonic flows is of interest in understanding the re/entry of space debris, meteoroid fragments, launch-vehicle stages and other rotating objects. Experiments were therefore carried out in the hypersonic wind tunnel H2K at the German Aerospace Center (DLR) in Cologne. A free-flight technique was employed in H2K, which enables a continuous rotation of the cylinder without any sting interferences in a broad angular range from 0$$^{\circ }$$ ∘ to 90$$^{\circ }$$ ∘ . A high-speed stereo-tracking technique measured the model motion during free-flight and high-speed schlieren provided documentation of the flow topology. Aerodynamic coefficients were determined in careful post-processing, based on the measured 6-degrees-of-freedom (6DoF) motion data. Numerical simulations by NASA’s flow solvers Cart3D and US3D were performed for comparison purposes. As a result, the experimental and numerical data show a good agreement. The inclination of the cylinder strongly effects both the flowfield and aerodynamic loads. Experiments and simulations with concave cylinders showed marked difference in aerodynamic behavior due to the presence of a shock–shock interaction (SSI) near the middle of the model. Graphic abstract

Investigation of the flight behavior of a flare-stabilized projectile using 6DoF simulations coupled with CFD

2019 ◽  
Vol 30 (9) ◽  
pp. 4185-4201
Author(s):  
Daniel Klatt ◽  
Michael Proff ◽  
Robert Hruschka
Keyword(s):  
Degrees Of Freedom ◽  
Rigid Body Dynamics ◽  
Flight Behavior ◽  
Free Flight ◽  
Aerodynamic Coefficients ◽  
Cfd Simulations ◽  
Time Resolved ◽  
Content Type ◽  
Six Degrees Of Freedom ◽  
Computational Fluid Dynamics Cfd

Purpose The present work aims to investigate the capabilities of accurately predicting the six-degrees-of-freedom (6DoF) trajectory and the flight behavior of a flare-stabilized projectile using computational fluid dynamics (CFD) and rigid body dynamics (RBD) methods. Design/methodology/approach Two different approaches are compared for calculating the trajectory. First, the complete matrix of static and dynamic aerodynamic coefficients for the projectile is determined using static and dynamic CFD methods. This discrete database and the data extracted from free-flight experiments are used to simulate flight trajectories with an in-house developed 6DoF solver. Second, the trajectories are simulated solving the 6DoF motion equations directly coupled with time resolved CFD methods. Findings Virtual fly-out simulations using RBD/CFD coupled simulation methods well reproduce the motion behavior shown by the experimental free-flight data. However, using the discrete database of aerodynamic coefficients derived from CFD simulations shows a slightly different flight behavior. Originality/value A discrepancy between CFD 6DoF/RBD simulations and results obtained by the MATLAB 6DoF-solver based on discrete CFD data matrices is shown. It is assumed that not all dynamic effects on the aerodynamics of the projectile are captured by the determination of the force and moment coefficients with CFD simulations based on the classical aerodynamic coefficient decomposition.

Free-flight tests of 10-degree cones with a one degree articulation angle

1999 ◽  
Author(s):  
Wayne Hathaway ◽  
Gerald Winchenbach ◽  
John Krieger
Keyword(s):  
Free Flight ◽  
Flight Tests

Subsonic/transonic free-flight tests of a generic missile with grid fins

2000 ◽  
Author(s):  
Gregg Abate ◽  
Ralf Duckerschein ◽  
Wayne Hathaway
Keyword(s):  
Free Flight ◽  
Flight Tests
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