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A Review of the Planform Effects on the Low-Speed Aerodynamic Characteristics of Triangular and Modified Triangular Wings

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A Review of the Planform Effects on the Low-Speed Aerodynamic Characteristics of Triangular and Modified Triangular Wings I NASA CONTRACTOR REPORT 7 N d I w U A REVIEW OF THE PLANFORM EFFECTS ON THE LOW-SPEED AERODYNAMIC CHARACTERISTICS OF TRIANGULAR AND MODIFIED TRIANGULAR WINGS &byKenneth Rum& and Melvin H. Snyder, Jr. Prepared under Grant No. NGR 17-003-002 by WICHITA STATE UNIVERSITY .. Kans. I_ Wichita, , ,, 2- . -. - _... for .,, . , .I . NATIONALAERONAUTICS AND SPACE ADMINISTRATION WASHINGTON,D. C. APRIL 1966 TECH LIBRARY KAFB. NY A REVIEW OF THE PLANFORM EFFECTS ON THE LOW-SPEED AERODYNAMIC CHARACTERISTICS OF TRIANGULAR AND MODIFIED TRIANGULAR WINGS By Kenneth Razak and Melvin H. Snyder, Jr. Distribution of this report is provided in the interest of informationexchange. Responsibility for the contents resides in the author or organization that prepared it. Prepared under Grant No. NGR 17-003-002 by WICHITA STATE UNIVERSITY Wichita, Kans. for NATIONAL AERONAUTICS AND SPACE ADMINISTRATION ~ ~ ~ ___~~ ~- For sale by the Clearinghouse for Federal Scientific and Technical Information Springfield, Virginia 22151 - Price 61.25 .. .. "-" CONTENTS Page Symbols V Abstract 1 Introduction 2 The Flow Field Abouta Triangular Wing 5 Methods of Analysis for Triangular Wings 16 Examination of Empirical Data 25 Bibliography 38 Figures 62 iii " ". SYMBOLS b2 A aspect ratio,A = - S a half-wing span at the chordwise station (ft. x cos a a i semispan of the ith rectangular wing (ft.) element section lift curve slope,-dC II aO da a.c. aerodynamic center b span of wing D cD coefficient of drag,gs Di cD induced drag coefficient, i s parasite drag coefficient,CD at C =O L coefficient of lift,-L cL qs an UL- - L = 0 cL slope of lift curve,CL - at CL a a da section lift coefficient M airplane pitching moment coefficient,- -Cma.c. cm qsc N q3 C local chord - mea n aerodynamic chord (ft.C aerodynamic chord mean 1 C 1 ro ot chord (ft. chord r root 1 ti p chord C t tip (ft. C section lift coefficient II c. p. center of pressure (% of E) D i nduced drag, D-DO drag,Di induced (lb. draglift at zero (lb-1 DO L lift (1b. li near dimension R linear (ft. V V M Mach number,M = 49.04 fi pitching moment abouta:c. Ma. c. N component of aerodynamic force normal to wingm.a.c. n fraction of distance between successive bound vortices n number of rectangular wing elements W wing semiperimeterP wing (ft.1 P pressure ft. (lb./sq. 1 pressure coefficient,pc - Plocal-Pfree stream 9 12 dynamic pressure, q = pV (lb./sq. ft.) R Reynolds number, R = PVk -F! airEoil section leading-edgeradius(ft. wing planform area planform wing (sq. ft.) absolutetemperature (deg.(freeair) R) t thickness(ft.maximumairfoil 1 airfoilthickness at chord station x (ft. 1 tx veloc ity (free-stream)V velocity (ft./sec.) local velocity (ft./sec.) velocity V local X distancemeasured in direction of free- (ft.1 stream velocity Y distancemeasured normal to free-stream (ft. 1 flow and parallelto wing span z distancemeasured normal to x and y (ft. 1 U (deg.angle of attack U angle of attack for which wing lift is zero (deg . L=O n r circulation, pod& ft./sec. (sq. ) Fourier coefficient 'n vi A increment 6 surfacedeflection angle E wingplanform semi-vertex angle e vortexshedding angle angle of sweepbackmeasured to the line A c/4 through the section quarter-chords sweepbackangle of the leading edge taper ratio, = ctr /c air density (slugs/cu. ft.) stream function vii ABSTRACT The fundamental aerodynamic phenomona of the flow around sharp leading edge triangular planform wingsis reviewed. Analytical methods of predicting lift character- istics of triangular wings are summarizedand experimental results of tests on wings of various planformare presented. A bibliography of 258 references is included. INTRODUCTION Aircraft designed for transonic and supersonic flight require the useof delta, double-delta, arrow,or other highly swept wings having triangular,or approximately triangular, planforms. The advent of the supersonic trans- port makes it mandatory that the aerodynamic characteristics of these wingsat low speeds be such that the airplane can use commercial airports. This usage requires accommodation in traffic control systems mixed with present generation jet aircraft traffic; therefore, the airplane must be tractable in the take-off, approach, and landing configur- ations. The prediction of flight characteristics in these operating configurations requires not only knowledge of C , L/D and CM variations at lift coefficients correspond- Lmax ing to approach and take-offspeeds, but it isalso necessary to be able to estimate side force andyaw derivatives, flow stability, ground effects, and the mannerin which these parameters are time-dependent in accelerated maneuvers. The airflow at low subsonic speeds(M < .3) about a triangular planform wing having a thin cross-section and sharp leading-edge isa complex mixtureof many flows which are individually definable but which, when interacting, are almost impossible to analyze. This complexity causes the triangular wingto differ distinctly from wings having larger aspect ratio, suchas the rectangularor tapered 2 .-. unswept wing and the conventional swept wing. Whereas unique procedures are available for the design and aerodynamic analysis of each of these foregoing wing types, the extreme complexity of the flow around a triangular atwing moderate or high angles of attack.(usually > 15O) has made it difficult to evolve either a singleor a combinationof theories which can.be dependably used for design. NASA has, from timeto time, surveyed and summarized the state of the art in certain aerodynamic areas. Notable reports are a summary of airfoil data(Ref. 1) , a surveyof swept wings (Ref. 1.00) and a review of the stall characteristics of swept wings (Ref. 2). The followilly report is a review of the state of the art with respectto the theoretical and experimental investigation of the aerodynamic characteristics of triangular or modified triangular wings. It has been deter- mined, unfortunately,tha.t it is not possible to present a complete summary, but an attempt has been made to give a des- cription of the physical phenomena of the flow on the basis that a more complete understanding of the qualitative flow field will assist in interpreting the summary data which has been collected. No attempt has been madeto evaluate any of the wing plan- forms as to their desirability for supersonic operation.It is presumed that the requirements for supersonic operation are 3 overwhelmingly predominant and the choiceof configuration will be madeto satisfy these criteria. It is probable that the configuration will be such that the flow will include such phenomena as leading-edge vortex shedding, streamwise boundary-layer separation lines, and a complex combination of trailing-edge vortex and conical vortex interaction. It might be said that this report pertains to those wings on which streamwise sheddingof vorticity from the swept leading-edge is the common characteristic andon which this shed vorticity radically affects the total flow pattern. This report consistsbasi.cnl.ly of two parts--first, a discussion and analysisof the flow field about triangular wings and the effectsof that flowon the low-speed aero- dynamic characteristicsof the wings, and, second, an analysis of published empirical datato determine wing planform effects on the aerodynamic characteristics. Classified material has not been surveyed in this summary study, and, therefore,very little of the latest test data on triangular or variable sweep wings has been included. Since extensive experimental work has occurred on different versions of theSST, it is presumed that a bodyof literature exists which will, at some later time, permit a correlation of some of the analytical and general theories with exper- imental results. This correlation is now not possible in an unclassified document. 4 TIIE FLOW FIELD ABOUT A TRIANGULAR WING Extensive literature is available, as seen in the bibliography (Refs. 8-58) in which methods are given to predictdCL/da, C , CD , Cm, and L/D character- Lmax' i istics of stra.ight wings, swc?pt wings, and even slender bodies serving as lifting surfaces.The work of De Young and Harper (Refs. 18, 19, and 20) extending and amplifying Weissinger's method of predicting span loadings and the work of Lowry and Polhamus (Ref.179) which further refines the method of estimating lift increments due to flap deflections are examplesof this well-developed literature. ,The work of Sacks, Nielson, and Goodwin (Ref.48) and Brown and Michael (Refs.11 and 12) giveadmittedly incomplete and approximate methodsof predicting the characteristicsof triangular planform wings. The aerodynamic featureof the deltaor modified delta wings which distinguishes them from other wings is the leading- edge shedding of vorticity. This feature is illustrated in the sequence of sketches in figure2 which diagramatically illustrate the manner in which vorticityis shed from a variety of wings. Figure 2(a) shows a rectangular plan wing witha series of bound vortices and spanwise continuous shedding of vortex filaments aligned with the local flow at the trailing- edge. A vortex filament is definedas a line along which the 5 entire vorticity of a vort.excan be assummed to be con- centrated, with the vector sense of vorticity determined bythe right-hand rule. The strengthof a vortex r = is identified as a vector directed along the filament. The spanloading of the wing is a measure of the strengthof the bound vorticity at all spanstations. With a non-uniformspan loading, the increment of loading, A(Cgc), betweenany two span stations is directly proportional to themagnitude of vorticity shed between those two stations. The vortex filaments must align with the local flow at the point of shedding,and eventually trail off downstream in thefree stream direction. The intensity,or density, of thevortex filament sheet is proportional to theslope of a tangentto the span loading curve at eachpoint along the span(dr/dy).
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