NASA NACA-TN-734-1939 Pressure-distribution investigation of an N A C A 0009 airfoil with a 50-percent-chord plain flap and three tabs《带有50%弦普通襟翼和三个标签的NACA 0009机翼的压力分布研究》.pdf
《NASA NACA-TN-734-1939 Pressure-distribution investigation of an N A C A 0009 airfoil with a 50-percent-chord plain flap and three tabs《带有50%弦普通襟翼和三个标签的NACA 0009机翼的压力分布研究》.pdf》由会员分享,可在线阅读,更多相关《NASA NACA-TN-734-1939 Pressure-distribution investigation of an N A C A 0009 airfoil with a 50-percent-chord plain flap and three tabs《带有50%弦普通襟翼和三个标签的NACA 0009机翼的压力分布研究》.pdf(43页珍藏版)》请在麦多课文档分享上搜索。
1、. . - - . . - - . .: Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-h .r NATIONAL ADVISORY COXMITTEE I- FOR AERONAUTICS - TECHEICAL NOTE NO. 734 - - . PRESSURE-DISTRIBUTION INVESTIGATION OF A!? N.A.C.A. 0009 AIRFOIL WITH A BO-PERCENT-CHORD PLAIN FLA
2、P AND TXREE TABS By Willfam G. Street and Milton B. Ames, Jr. SUMJARY Pressure-distribution tests.of an N.A.C.A. 0009 air- s foil with a 50-percent-chord plain flap and three plain - tabs, having chords 10, 20, and 30 percent of the flap chord, were made in the N.A.C.A. #- by 6-foot vertical tunnel.
3、 The tests supplied aerodynamfc section data that may be applied to the design of horizontal and vertical tail surfaces. . The results are presented as resultant-pressure dia- grams for the airfofl with the flap and the 20-percent=- - - chord tab. Plots are also given of increments of nbr-mZl- - for
4、ce and hinge-moment coefficients for the airfoil, the flap, and the three tabs. The experimental results and values computed by analytical methods are in good agree- _. Y ment for small flap and tab deflectfons. The results of the tests indicated that the effectiveness of all three tab sizes in redu
5、cing flap hinge moments decreased wi;th increasing flap deflection. - .- _- l INTRODUCTION - ,. . The recent increases in speed and. size of airplanes have produced excessive control fo,rces. - - At the preraent time, one of the most effective devices for r8dUCing these high control forces is the tr
6、aglinq-edge tab. (Sea refer- -z ences 1 and 2.) Previous investigations have indicated -* the effects of such factors as plan form, cut-cuts, 8nd . I plates, elevator nose shape, gap, and balance on the aero- I -. _ dynamic characteristics of some tail surfaces of.finite span (references 3 and 4). P
7、O available data applicable to tail-surface design, however, give the section aerody- _ -A (“ - _ - .-. - Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2 N.A.C.A. TechnicalNo-to lVo. 734 namic characteristics of a thin airfoil as affected by flaps
8、and tabs. The present investigation was therefore undertaken to supply information that would be applicable for use in aerodynamic and stmFnctura1 design of tail sur- faces w?th tabs. The tests consisted of pressure-distribution measure- ments over one section of an N.A.C.A. 0009 airfoil with a 50-p
9、ercent-chord plaih flap and with plain tabs 10, 20, and 30 percent of the flap chord. From the data obtained, normal-force and pitching-moment coefficients were calcu- lated for the airfoil section complete with the flap and the various tabs. In addition, normal-force and hfnge- moment coefficfents
10、were calculated for the flap nith the different tabs and for the tabs alone. APPARATUS AND TESTS Mod-e1 and Test Installation The tests were conducted in the N.A.C.A. 4- by 6- f%ut vertical wind tunnel. This tunnel, originally a 5- foot open-jet vertical wind tunnel (reference 51, has recently been
11、modifie- - L - i p*p-Po 9 .- - .I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 M.A.G.A. Technical Bate No. 734 P is static pressure at a point on the aFrfoi1, c PO static pressure in the free air stream. 99 dynamic pressure of the free sir strea
12、m. In order to enable the designer to obtain the origi- nal resultant-pressure diagram for any condition, resultant- pressure diagrams are qiven for the basic section (i.e., flap and tab neutral, fig. 4) which, when added to the fn- crement diagrams (figs, 5 to 10) oive the desired result. Because t
13、he large quantity of data prohibited the fn- elusion of the resultant-pressure-increment diagrams for all tab sizes, only the diagrams for the 0.2Ocf tab, which was consfdered to be an averase size, are presented. Val- ues of angle of attack were also selected to re resent the negative angle-of-atta
14、ck condition, a = -9 ; P the LOW angle-of-attack condition, cz = 1/2O; and the PO 8 itive angle-of-attack condition, cx = 5*“. The value of 59 may seem rather low; but, with such a large-chord flap, the stall occurs at low angles of attack. The section characteristics of the airfoil, the flap, and t
15、he tab, as functions of flap and tab deflection, are also plotted as increments, which were obtained by deduct- ing the basic section coefficients from those for the sec- tion with the tab, the flap, or the combination deflected. The characteristics were obtained in each case by mechan- ical integra
16、tion of the original plotted pressure diacrams. Computations were made to determine the section coeffi- cients, which are defined as follows: c I cn n = yy , airfoil section normal-force coefficient. m rn = -, 9 c= -airfoil section pitching-moment coefft- cient about quarter-chord point of airfofl.
17、nf Cnf = -I flap section normal-force coefficient. c 4. c-f ch hf f = -:, flap section hfnse-moment coefficient. q Cf * Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-N.A.C.A. Technical Note No. 734 5 Cnt nt = -* tab section normal-force coefficient
18、. q ct Cht = - tab section hinpe-moment coefficient, 9 ct= where the n, m, nf hf nt ht and Cl Cf* Ct 1 forces and moments per unit saan are: normal force of airfoil section. , pitching moment of airfoil section about the . quarter-chord point. I normal force of flap section. hinge moment of flap sec
19、tion. - normal force of tab section. : hinge moment of tab section. chord of basic airfoil with flap and tab neutral. flap chord. tab chord. The subscript f refers to the flap with the tab; and the subscript t, to the tab alone. In figure 11, the integrated coefficients for the basic airfoil are plo
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