NASA NACA-TN-1191-1947 Two-dimensional wind-tunnel investigation of four types of high-lift flap on an NACA 65-210 airfoil section《NACA 65-210翼剖面上四种类型高升力襟翼的二维风洞研究》.pdf

1、NATIONAL ADVISORY COMMITTEEFOR AERONAUTICSJTECHNICAL NOTENo. 1191TWO-DIMENSIONAL WIND-TUNNEL INVEaTIGATIONOF FOUR TYPES OF HIGH-LIFT FLAP ON ANNACA 65-210 AIRFOIL SECTIONt_ii By ones F. CahilltLangley Memorial Aeronautical LaboratoryLangley Field, Va.WashingtonFebruary 1947i i i ii t/BUStNE6S,SCIENC

2、E“ i.,i-_ +!.: i! ;!; :hewn it, :isu.rc l(b), ih0 refc, rcnc: ;r:o:_n%si on,-;, rj%0.03e mePs,z4,iro_!i Sb.e iet-:!.i_ b: 0!_ of sbS,ll_.a.rd. “:/“ _i_ reference 4.I _C,r_CYP-Pe7 im-ln%_v., to.i-s o_ _-_-d.,.:rood.e, w_t.h._eat!l of/._he fle.ps I6re. ,_ _ .0 ,.o_ th:,/_.upo,_in 10*-_-“:_“_u of the w

3、:tn_“sta_lod. No o uc improv,e_oni: wc_s n.ot,.:_d in ,_hosmooo,:_.COD.dJ._JJ.oII.This _i._,.,_,is net.cod in t_,_d.i_t_,dbbeine,i with _,_c_ of the f.-_s,but is very sliJ_.tw:l.tithe t.,.oub_os:kotbe,9,i_-p._om“tests inthe _-,_,m_o_ho condition the model was t,_p,_“ w:.ry s.raooblz “_a_,d-“eco,lrs,

4、 to.yto oonbouz. _.1_o d.iscu_sion of _-_ ; (, ut,r.-_b_c_ Of I01.$11aa_._oz_,_o_ :“g nofs ox,.Z:.-;tf-:.:_.:_.,.d. _ tb _ “._._., . _r _ :./,. “%i, b.i _:.c,:an _,.:.mS with, _ _ c,iL1_:-b:_r,.002 _,2.,:_,?“_:.Z:“.:1,_,_._?.:._ ga,?k_ i:L0?bo_ 0ohn,M.: . _ _ :“_ “ “_“ ,.-:_d. WISlotted flap 10.900c

5、coo_oline Flap chord line -0.250c _JrISlotted flap 20.975codAirfoil chord line _ _ _ : _ ! -0“250c _ISlotted flap 3,._I o.84ocoho 0Airfoil chord llne / _ ._J/o“ / _ Main-flap chord line- - /f _ -_ + _ Z i !_o.31ac . ,4Double slotted flapNATIONAL ADVISORYCOMHITTEEFORAERONAUTICS(a) Flaps tested.Figure

6、 i.- Sketch of flaps tested on NACA 65-210 airfoil section.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1191 Fig. ib“ _e-flaP chord llne -% _ _2 6fT-COMMITTEEFOaAERONAUTICSO(b) Variables used to define flap configurations.Figure 1.- Oo

7、ncluded,Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig, 2a NACA TN No. 1191 .o 1.2 ,0o I _ ttL/ o63 x 106“4 “_ o 9gz_ Standard rc ghneaso 6 x 1061, _ _4.J= 0 0hO 0 / i! ,2k !0i, “ L.,-4.4 _ NATIONAL ADV ;ORY0 I COMMITTEEFORAER)NAUTICS0 0 _._ I l

8、-16 -8 o 8 z6 z4.Section angle of attack, ao, deg(a) Plain airfoil.Figure 2.- Section lift and pitching-moment characteristics of theNACA 65-210 airfoil section. (Reference 4.)Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1191 Fig. 2b2.

9、0o 1.6 / ,.1_“001.2o Ro 2 xlO 6_4.8 0_ _ Standard rou_ness.,46 x 106i/,oIDo.r.t_ , 0.,-t0 _._ NATIONAL ADVISORYO.“._1- fnMMITTF FOR AERONAUTICS-16 -8 0 8 16Section angle of attack, _o, deg(b) Airfoil with 0.20c split flap. Of = 60.Figl._e 2.- Concluded.Provided by IHSNot for ResaleNo reproduction or

10、 networking permitted without license from IHS-,-,-OqOD1_ ,2.50. “_36 5 4 3 2 o -i_ _ NATIONAL ADVISORY 2.HFigure 3.- Contours of values of maximum llft coefficient for maln-flap positions with respect to fore-flap trailing edge.Double slotted flap; NACA 65-210 airfoil; R = 2._ l06 (approx.); 8ff =

11、25o; Xl = 0“9; Yl = 1“9; Gf = 50o .F-LProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-C_“ o_21 !_e j 12.BO. NATIONAL ADVISORYCOMMITTEE FOIt AERONAUTICS- CT,maX-6 “ZB CL_ - j_?.4 3 2 z o -x -a -3Xl, percent o(a) 8f = 20 .Figure 2.- Contours of values

12、of maxlmtml llft coefficient for positions of main flap and fore flap as a unit at various flapdeflections. 0.312c double slotted flap; NACA 65-210 airfoil; R = 2._ 106 (approx.).0_Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-#-i-_oo_0 -2 (J_ f2.!

13、- _ _.sc_ NATIONAL ADVISORY,.,._ _ CONNITTEE FORAERONAUTICS565 4 3 2 I o -i -2Xl_ percent c0_o(b) 5f=45.Figure 4.- Continued. _DProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-g0o_0. _-_1 _D_2x 1 percent c _NATIONCOMMITTEE FORAERONAUTICS(c) _f = 500

14、. _Figure _.- Continued. OqOProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-oe.-IProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-g_Oc?, “ 2,62_ I-_2 2.20- _ 3 _ 3 2 zXl, percent cGCONmTTEFOQ_ONALrrtcs

15、 6f = 60 . _(e)Figttre _.- Concluded. “_ 0_(D6.JProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-!70qcDq0 Io _ ,c_max .90 200 _2 I 2.26 5 _ 5 2 z o -zX, percent cNATIONAL ADVISORY _COMMITTEE FOIl AERONAUTICS _(a) 6f = 30 .Contours of values of maximum

16、 llft coefficient for positions of slotted flap i at various flapFigure 5.-deflections. NACA 65-210 airfoil; R = 2._ x l06 (approx.). oProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-f O- c_33 2 i cx, percentNATIONAL ADVISORYCOMHITTEE FORAERONAUTICS(

17、b) _c= L_O“Figure 5.- Continued.0_Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA 65-210 airfoil; R = 2. 2 x 1O 6 (approx.).Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-C)o_0 _233 2 i o -zx, p

18、ercent cNATIONAL ADVISORYCOMMITTEE FO_ AERONAUTICS(b) 6f = 36.3 .Figure 6.- Continued.(DProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-/Oq06 5 _ 5 2 1 0 -1 _-2x, percent cNATIONAL ADVISORYCOMMITTEE F_ _RONAUTICSQ(c) _ = _1.3. _Figure 6.- Continued.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-