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

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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-,-,-