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首頁(yè)> 美國(guó)政府科技報(bào)告 >WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC SPEED OF THE STATIC LONGITUDINAL STABILITY CHARACTERISTICS OF AnWINGED REENTRY VEHICLE HAVING A LARGE NEGATIVELYnDEFLECTED FLAP-TYPE CONTROL SURFACE
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WIND-TUNNEL INVESTIGATION AT HIGH SUBSONIC SPEED OF THE STATIC LONGITUDINAL STABILITY CHARACTERISTICS OF AnWINGED REENTRY VEHICLE HAVING A LARGE NEGATIVELYnDEFLECTED FLAP-TYPE CONTROL SURFACE

機(jī)譯：具有較大負(fù)偏壓的扇形控制面的懸掛式再生車輛靜態(tài)縱向穩(wěn)定性特征的高次聲速風(fēng)洞隧道研究

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摘要

An investigation has been made in the Langley high-speed 7- by 10-foot tunnel to determine the feasibility of using a flap-type control surface to provide longitudinal trim and stability throughout an angle-of-attack range from -2° to 90° on a clipped-delta-wing configuration, having an aspect ratio of 1.12, a taper ratio of 0.29, and a leading-edge sweep angle of 63°, considered for reentry from satellite orbit. The model was tested at Mach numbers- from 0.60 to 0.90 with correspondingnReynolds numbers of 2.76 x 10° to 4.03 x 10° based on the basic-wing mean aerodynamic chord. The control surface consisted of a large trailing-edge flap that extended outboard of the wing tips. Vertical tails attached to the control surface at the wing-tip station moved with the control surface.nThe control arrangement provided longitudinal trim and stability over most of the angle-of-attack range. However, the configuration was unstable at angles of attack from approximately 12° to 2k°, especially at the lower Mach numbers.

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    Paul G. Fournier;

  • 作者單位
  • 年度 1959
  • 頁(yè)碼 1-22
  • 總頁(yè)數(shù) 22
  • 原文格式 PDF
  • 正文語(yǔ)種 eng
  • 中圖分類 工業(yè)技術(shù);
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