Influences of sway braces and mounting gaps on the static aerodynamic loading of external stores

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086 0 ⊔ ‡aD 301.45/33: 77-117
100 1 ⊔ ‡aDix, R. E., ‡eauthor.
245 1 0 ‡aInfluences of sway braces and mounting gaps on the static aerodynamic loading of external stores / ‡cR.E. Dix.
264 ⊔ 1 ‡aArnold Air Force Base, Tennessee : ‡bArnold Engineering Development Center, Propulsion Wind Tunnel Facility, Air Force Systems Command, United States Air Force, ‡c1978.
300 ⊔ ⊔ ‡a69 pages : ‡billustrations ; ‡c28 cm
336 ⊔ ⊔ ‡atext ‡btxt ‡2rdacontent
337 ⊔ ⊔ ‡aunmediated ‡bn ‡2rdamedia
338 ⊔ ⊔ ‡avolume ‡bnc ‡2rdacarrier
490 0 ⊔ ‡aAEDC-TR ; ‡v77-117
500 ⊔ ⊔ ‡a"February 1978."
500 ⊔ ⊔ ‡a"Final Report: October 1, 1976 -- September 30, 1977."
504 ⊔ ⊔ ‡aIncludes bibliographical references (page 15).
520 ⊔ ⊔ ‡aAs 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).
536 ⊔ ⊔ ‡aReport supported by the Air Force Systems Command and prepared by ARO, Inc, under Program Element, ‡e65807F.
538 ⊔ ⊔ ‡aMode of access: Internet.
650 ⊔ 0 ‡aPhantom II (Jet fighter plane)
650 ⊔ 0 ‡aAerodynamics, Transonic.
650 ⊔ 0 ‡aAerodynamic load.
710 1 ⊔ ‡aUnited States. ‡bAir Force. ‡bSystems Command, ‡eissuing body.
710 2 ⊔ ‡aArnold Engineering Development Center, ‡esponsor.
710 2 ⊔ ‡aARO, Inc., ‡esponsor.
730 0 ⊔ ‡aTechnical Report Archive & Image Library (TRAIL)
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