欢迎来到麦多课文档分享! | 帮助中心 海量文档,免费浏览,给你所需,享你所想!
麦多课文档分享
全部分类
  • 标准规范>
  • 教学课件>
  • 考试资料>
  • 办公文档>
  • 学术论文>
  • 行业资料>
  • 易语言源码>
  • ImageVerifierCode 换一换
    首页 麦多课文档分享 > 资源分类 > PDF文档下载
    分享到微信 分享到微博 分享到QQ空间

    REG NACA-RM-L9C23-1949 High-subsonic damping-in-roll characteristics of a wing with the quarter-chord line swept back 35 degrees and with aspect ratio 3 and taper ratio 0 6.pdf

    • 资源ID:1017486       资源大小:380.23KB        全文页数:22页
    • 资源格式: PDF        下载积分:10000积分
    快捷下载 游客一键下载
    账号登录下载
    微信登录下载
    二维码
    微信扫一扫登录
    下载资源需要10000积分(如需开发票,请勿充值!)
    邮箱/手机:
    温馨提示:
    如需开发票,请勿充值!快捷下载时,用户名和密码都是您填写的邮箱或者手机号,方便查询和重复下载(系统自动生成)。
    如需开发票,请勿充值!如填写123,账号就是123,密码也是123。
    支付方式: 支付宝扫码支付    微信扫码支付   
    验证码:   换一换

    加入VIP,交流精品资源
     
    账号:
    密码:
    验证码:   换一换
      忘记密码?
        
    友情提示
    2、PDF文件下载后,可能会被浏览器默认打开,此种情况可以点击浏览器菜单,保存网页到桌面,就可以正常下载了。
    3、本站不支持迅雷下载,请使用电脑自带的IE浏览器,或者360浏览器、谷歌浏览器下载即可。
    4、本站资源下载后的文档和图纸-无水印,预览文档经过压缩,下载后原文更清晰。
    5、试题试卷类文档,如果标题没有明确说明有答案则都视为没有答案,请知晓。

    REG NACA-RM-L9C23-1949 High-subsonic damping-in-roll characteristics of a wing with the quarter-chord line swept back 35 degrees and with aspect ratio 3 and taper ratio 0 6.pdf

    1、1-wsr- f.AL .“ RM NO. L9C23 - “_ “ “- - 1 RESEARCH MEMORANDUM HIGH-SUBSONIC DAMPING-IN-USLL CHARACTEF?STICS OF A WING WITH THE QUARTER-CHORD SWEPT RACK 35 AND FOR AERONAUTICS WASHINGTON May 10, 1949 UNCLASSIFIED Provided by IHSNot for ResaleNo reproduction or networking permitted without license fro

    2、m IHS-,-,-UNCLASSIFIED By Boyd C . Myers, n: and Richard E. Kuh An investigatim of the dmping-in-roll characteristics of a 35 swept- back wlng, with and without vertical fins, hae been made through a Mach nmber range of 0.40 to 0.91 in the Langley hi-speed 7- by 10-foot tunnel utilizfng a free-to-ro

    3、ll technique. “ I The damping-in-roll coefficient increased Fn magnitude with Mach number in the manner, indicated by theory ad gmerallg was found to increase Fn ma-tude with angle of attack over the range tested. Bertical fins located at about the Ldspan etation of ewh w3n.g panel had little effect

    4、 on the damping-in-roll characteristics of the wlq but increased the aileron effectiveness in prod-ucing rolling mcrmeat. - h eXt013iVe inve8tigatiOll Of the effect8 Of Cm8Eibility CM the dmping-in-roll chmacteristics of various wlng plan forme is being conducted in the Langley high-speed 7- by 10-f

    5、oot tunnel. The 35 swept back wing of aspect ratio 3 and taper ratio 0.6 anployed in the present of the tailless -1 reported in reference 1. The present investigaticn was carried out on a free-.rotating appesatus with the purpose of deter- mining the effects of compressibility and angle of attack (M

    6、 the dampw in-roll characteristics of the wing, with and without the vertical fins that were wed on the taflless model reported in refermce 1. bT06tigatiOIl W positive deflection down, degrees pb/2V ang-tlp helix e, radians , Provided by IHSNot for ResaleNo reproduction or networking permitted witho

    7、ut license from IHS-,-,-3 Subscripts : “2 left ailercm ar right aileron The pertinent dimensions of the ateel wing, ailerans, and vertical fins are given fn figure 1. The ailercms were of true cmtour and constant chord and had sealed-noee gaps. The ordinates of the sym- metrical airfoil sectian, whi

    8、ch is not a standard NACA sectim, am given Fn table I. The model was supported by a at- extending forward into the test sectim from a vertical strut located behind .the del. The vertical strut ms part of the wind-tmnel balance eytern and both the strut and a portion of the sting were ehielded fram t

    9、he air stream by a fairing. A schematic drawing of the support system and rolling apparatus is whereas, the fins-on Configuration was tested only at an ElngLe of attack of 0.3dJ However, both-configurations were tested thro as aileron-deflecticm range of o0 to fg .4 and nly the left ailerm was defle

    10、cted. The size of the model used in the present investigatian resulted h an estimated chow Mach nuonher of 0.94 and the data axe believed to be reliable to a corrected Mach nuuiber of about 0.91. The vmiatfm of test Reynolds number wlth Mach nmber for average test cmditions is presented in figure 4.

    11、 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 correc tione NACA RM NO m LW23 A Ermall tarre correctim in the form of bearing friction was applied to the results a6 S AND DISCUSSION The results are presented in the following figuree: Baafc force

    12、data Cz plotted ae, especially at higher Mach nmibers . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6 L, NACA RM NO. 9223 3. Vertical fine, mounted at approximately the midepan section of each wing panel, had little effect an the damping-Fn-roU.

    13、characteristics of the wing but increased the effactiveness of the ailerons in producing rolling moment. L Langley Aeronautical Laboratory National Advisory Committee for Aeronautics Langley Air Force Base, Va . 1 Dcmlan, 9harles J ., and Kuhn, Richard E .: Estimated Transonic Flying witlee of a Tai

    14、llese Airplane Baaed, on a Model lhvestigatlon. NACA RM No. 908, 1949. 2, Herriot; John G. : Blockage Correctima for Three-Dimenelanal-Flow Closed-Taroat Wind T-els, with Consideratian of the Effect of Compressibility. HACA RM mo. 728, 1947. of Swept WbgE in ROU and stdesup. NACA m NO. 3 1 39, 1949

    15、8 3. Bird, John D.: Scape Theoretical Low-Speed Span Load Characteristics 4. QueiJo, M. J., and Lichtenstein, Jacob H.: The Effects of High-Lift Devices on the Low-Speed Stability Characteristics of a Tapered 37.5O Sweptback Wing of Aspect Ratio 3 in Straight and RollFng Flow. XACA RM No. L8I03, 194

    16、8. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Ordinate, fg 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. TAWLATED DATA Wirg Am Apct mtb Mem otm?ynamk chmi OiMml Tws mtlo Alrfdl (Table I) ha

    17、tion 0fm.thlckneSs lwmimum thkkness 3.17911 ff 3.0 0“ ID5ft 0.6 039c symehiclicol amc . Vatical fins Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-* . -. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-

    18、,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. -. . . . . . . , . * . . . , 1 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permit

    19、ted without license from IHS-,-,-. . I I . . . . . . . . . . . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-14 IWA RM HO. 14x23 G - 4 .5 .6 .7 .8 .9 LO a;: 650 Much number, A Figure 5. - Variation with Mach number of the roklxx-mcxnent charact

    20、eristics of the teet wing far varioue angle8 of attack and aileron deflectfane; vertical flm off; “-= 0. - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I I .O/ 0 -n I .S .6 .7 .8 Mach number, M $1 N W Provided by IHSNot for ResaleNo reproduction o

    21、r networking permitted without license from IHS-,-,-16 . -. “ . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-v t. a4 -5 .6 .7 .B .9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 .5 6 .7 8 .9 h

    22、vertical fins off. . - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.4 .5 .6 .7 .8 .9 LO Much number, A4 Figure 10.- Effect of the vertical fins on the aileron effectivenem; - a = c.30. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . N 0 .5 -7 .8 .9 , . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . . . . . . . . . a I B Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-


    注意事项

    本文(REG NACA-RM-L9C23-1949 High-subsonic damping-in-roll characteristics of a wing with the quarter-chord line swept back 35 degrees and with aspect ratio 3 and taper ratio 0 6.pdf)为本站会员(dealItalian200)主动上传,麦多课文档分享仅提供信息存储空间,仅对用户上传内容的表现方式做保护处理,对上载内容本身不做任何修改或编辑。 若此文所含内容侵犯了您的版权或隐私,请立即通知麦多课文档分享(点击联系客服),我们立即给予删除!




    关于我们 - 网站声明 - 网站地图 - 资源地图 - 友情链接 - 网站客服 - 联系我们

    copyright@ 2008-2019 麦多课文库(www.mydoc123.com)网站版权所有
    备案/许可证编号:苏ICP备17064731号-1 

    收起
    展开