1、 RESEARCH MEMORANDUM - .,j ; TESTS OF A TRL%NGU$%R WING OF ASPECT RATIO 2 IN THE AMES 12-FOO/T-PRESSURE WIND TUNNEL. III -THE EFEChVENESS AND HINGE MOMENTS OF A SKEWED WING-TIP FLAP By Carl D. Kolbeand Bruce E. Tinling Ames Aeroimutical Laboratory Moffett Field, Calif. ClASS1FtCATlON CANCECLF3 NATIO
2、NAL ADVISORY COMMITTEE FOR AERONAUTICS WASHINGION September 21, 1948 lAWL02was Awing-tip flapwiththe hinge line swept tested on a semispan mdel of a tr ianguLar wing of aspect . Flap effectiveness aad hinge smments w8re m8sUred at Mach numbsrs up to 0.95. SYMBOLS -CD ch CL c, M R S V W drag coeffici
3、ent lift. coefficient pitching4nomant coefficient 8bOUt the quarter-chord point of the wi,ng mean aerodynsmic chord pitching moment qSc Reynolds nungle of attack is increased. 5 rate Of change of hinge4maent coefficient with lift coeffioient is whereas data for the skewed w-tip flap indicate a reduc
4、tion in lif%drag ratio when the flap is defleoted. Figure 12 pesents.the variation of lift, pitoting- nt, and I. hingeamnt coefficient with flap deflection for 0 angle of attack at several Wch numbers. Flap effectiveness and hinge mmnt are approximately linear at O“ angle of attack-for t;he range of
5、 flap deflections, An increase in Mach number caused an increase in the absolute values of the slopes of these curves, The lift effective- m88 a whereas the value of however, due to the large 1 static stability the flap would be ineffective in balancis the airplane to even E moderate lift coefficien
6、t. = KFILTCATIOlV OF DATA - The data of this report have been applied to the calculation of the levelcflight characteristics of a hypothetical tailless airplane equipped with a triangular wing geometricl.4 similar to the model wing. The dimsnsions of the airplane were assumed to be as follows: WiIlg
7、ar8E,“.D 500 sq ft wirIgspan; .,. l . . . . l * . . . . . . . . . . . 31.91rt Control-surface area . . . . . . . , . . . . . . . D 102.25 sq ft , Control-hinge mcrnrent . . ; . . . . . . . . . . . . 612.6 ft-lb - Cenrofgravity., 0.32 M.A.C. * With the exception of the type of control surface and the
8、 absence of a fuselage, the hypothetical airplane is identical with that employed - , -=i Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA HM No, A8N21 7 in the calculations of reference 1. Since the data of reference 1 . indicate that the additi
9、on of the body caused only minor changes in . the wing characteristics, the results of these calculations can be . compared directly with figure 29 of reference 1. 5 lift coefficient, flap defl8ction, and hinge moment required for level flight at an altitude of 30,000 feet are presented in figure 17
10、 for wing loadings of 40, 60, and 80 pounds per square foot. Stick-fixed stability is seen to exist at all . of the mean aerodynamic chord would be mny timsa greater than the control forceB wfth the conick-free neutral point with the skewed . wing-tip flap W ma, c;lolst R, q2oqoOO. Provided by IHSNo
11、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. . , ! 42 -8 -4 0 4 8 12 16 20 24 Angk of otiack, Q, degrees -08 .04 0 704 708 Figure 5.- ?3e aerodynamic characleri
12、stics of a triangufar wing for VU R, 3,200,OOO. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-20 NACA RMNo. A R, 3,200,OOO. I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA FM No. A8EZ3 21 -8
13、-4 0 4 8 /2 I6 Angle of offock, Q, degrees -.08 .04 0 704 -.08 Pif.hfng-moment coefficienf, Cm 0 0 0 -4 V -8 a -/2 V -/6 n -22 0 -26 .2 ./ 0 4 4 0 .04 .O8 ./2 Hinge- moment coefficienf, Ch Dmg coei%tkn CD figure 8.- The uerodynmic churucterisfics of u friongdur wing for vufious f/up ungies. rw, 0.90
14、0; #?, 3,200,OOO. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-8 -8 -e-u- -_- -mm-_ -w-m I I -.4 -2 0 .2 .4 .6 .8 -.2 0 2 .4 74 -.2 0 .2 .4 LIT7 coeffiS c, . Figure It- The variutim of hft-drag ratio with kft coefficient for a frionguior wing havi
15、ng a skewed wing-tip flap at several Mach tWf?.Tbe?S. R, R, q200,OOO. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-26 IWARMNo. A8lZ21 .024 .0/6 CofHonf -chord f/op (fef: I - - - - I I t t I t t t I Meosuf ed f hrough 6 = O” I I I I I I I -.008 - I
16、 I I I I I l l l l -. O/6 -.02 .3 4 . .5 .6 ? . .q .s 1 I I r Figufe /3.- The variufion of fbe effectiveness of a skewed Wing- # fip flap and 0 consfanf- chord f/up wit/t Mach number . on a friunguh wing mode/. a, 09 c Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-27 -Al36 -.032 -.024 l-t Skewed wing-f f/op Consfonf - chwd flop fief /I - - - - H-i and -.0/6 I i I I I _ I I I I I I I I I I I I I -I I I I n -.0/z 0” -l- R,5,000,000. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
