Comparison of Wind Tunnel and Flight Test Measurements of Static Aerodynamic Loading of a Captive Store PDF Download
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Author: R. E. Dix
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 122
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Book Description
Author: R. E. Dix
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 122
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
A coordinated series of experiments was conducted in three wind tunnels and in flight to measure the static aerodynamic loading of a MK 83 store attached to the bottom center station of a triple ejector rack mounted on the left inboard pylon of an F-4 aircraft. Fundamental agreement between wind tunnel and inflight loads data was demonstrated over a range of angle of attack from -2 to 6 deg and a Mach number range from 0.6 to 0.9. Differences that were noted were thought to be attributable either to improper store-to-aircraft alignment or to poor definition of inertial loads during maneuvering flight. (Author).
Author: A. R. Maddox
Publisher:
ISBN:
Category : Loads (Mechanics).
Languages : en
Pages : 46
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1278
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 952
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 24
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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In a series of wind tunnel tests, measurements were made of the aerodynamic loads acting on eight different store configurations supported in and near the external captive position on a 1/20-scale model of the F-4C aircraft. Store models included blunt and contoured afterbody shapes, stable and unstable configurations, and large (pylon-mounted) and small (rack-mounted) configurations. Six components of forces and moments were measured using two methods of supporting the store models: an internal bracket support technique (IBS), and a dual sting support technique. Some characteristics of the interference flow field of the aircraft were also inferred.
Author: R. E. Dix
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 140
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Book Description
As the scale factor applied in the design of wind tunnel models is reduced, many details of the configuration being simulated are customarily omitted. A series of experiments was conducted in the Aerodynamic Wind Tunnel (4T) of the Propulsion Wind Tunnel Facility at the Arnold Engineering Development Center to evaluate the effect on captive store loading of model details such as sway braces and mounting gaps existing between store and aircraft components. Six components of aerodynamic loads acting on both pylon- and rack-mounted stores in the captive position were measured, a limited number of store separation trajectories was predicted using the captive trajectory system, and a brief comparison of wind tunnel and in-flight measurements of captive loads was made. It was determined that the effects of mounting gaps or flow ventilation passages were generally small, but that sway braces can significantly influence both captive loads and separation trajectories. It was also observed that better agreement between wind tunnel and in-flight measurements of captive store loading resulted when mounting gaps and sway braces were simulated on the wind-tunnel models. (Author).
Author:
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Category :
Languages : en
Pages : 0
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A series of flight tests were made to acquire captive loads data on a store to compare with corresponding data from several wind tunnel tests with conditions matched as closely as possible as well as with the best mathematical models available. The store consisted of a Mk 83 bomb shape mounted on a triple-ejector rack (TER) on an F-4 aircraft which was instrumented complete with a standard research boom mounted on the nose. The flight conditions spanned Mach 0.6 to 0.9 in both maneuvering and steady flight. The data show good correlation between flight test and wind tunnel for moderate subsonic Mach numbers when good geometric similarity is maintained, but there is a pronounced divergence in this agreement as the Mach number is increased. Correlation between mathematical models of this problem and the flight test show the same magnitude in loads and moments, but the trends do not always agree. This is most pronounced in the pitch plane.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 442
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