NASA NACA-RM-L54F25-1954 Effects of canopy revised vertical tail and a yaw-damper vane on the aerodynamic characteristics of a 1 16-scale model of the Douglas D-558-II research air.pdf

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1、RESEARCH MEMORANDUM EFFECTS OF CANOPY, REVISED VERTICAL TAIL, AhD A YAW-DAMPER VANE ON THE AERODYNAMX CIHARACTENSTICS OF A l/Is-SCALX MODEL OF TEE DOUGLAS D-558-11 FLESEARCII AIRPLANE AT A MACH NUMBER OF 2.01 By -Ross B. -%binson LO$lFI DENTlAL Provided by IHSNot for ResaleNo reproduction or network

2、ing permitted without license from IHS-,-,-E“XA RM L9F2j EFFZCTS OF CJXOPY, REVISED VEXIIC-AL TAIL, AND A YAW-D- VANE ON !FIB AERODYK4MTC CHPRACT!ERiSTICS OF A 1/16-scm HODEL OF THE DOUGIAS D-5g-n RESEARCH AIRPLLLWE AT I! MACH NLpMaER OF 2.01 By Ross B. Robinson I The aerodynesic chzzacteristics in

3、pitch and sideslip of r. revised 1/16-scale model of the Douglas D-558-11 research airplane, with and without a yaw-damper vme, me presented for a Wch nmber of 2.01. The to sinulate more closely the present, airplme configuration. The model was tested through m mgle-of-attzck range 013 -2O to about

4、13O at an angle of sideslip ol 0 md an- angle-of-sideslip range of -2O to about loo at an mgle of attack of Oo. The results .zre compared wiYn those previously obtahed for the origind model configuration. - revised model incorsorated a canopy md a modified vertical tail in order Tne revised configur

5、a-lion had higher directional stability, trin lift coefficients, and drag urd more positive effective dihedral thm the original configuration. The stetic longitudinal stability, the lift-curve slope, snd the effectiveness of the horizontal stabilizer were not siggif- icmtly altered by the changes in

6、 configuration. The vane effectiveness pzremeter increased rapidly with c% increasing lift coefficient and but only slightly with angle of sideslip. INTRODTJCTiON Various investigations have been conaucted that are concerned with the aerodynamic charzcteristics of the Douglas D-558-11 reseerch airpl

7、ane which is currently undergoing flight tests by the NACA Hi . Mach number variation Flow angle in horizontal or vertical plane, deg . 100 to. 015 kO.1 CORRECTIONS AND -4CCUR4CY The mgles of attack ad sideslip were corrected for the deflection of the bahce end sting under load. No corrections were

8、applied to the data to accouat for the tunnel flow vuis.tions. The base pressure was measured and the longitudinal force data xere corrected to a base ?res- sure equal to the free-stream static pressure. The estimated errors in the data me: CL . cx . cy. cm . Cn . cz . it, deg a, deg . 6, deg . . 20

9、.004 fO .002 20.002 to. 0007 to. 0005 C0.0003 20.1 20.1 kO.1 PRESENTATION OF RESULTS The results of this investigation are presented in two sections: (1) the effects of the canopy end revised vertical tail OD the aerodynaaic characteristics of the model md (2) the characteristics of the yaw- dpmper

10、vane in pitch uld sideslip and the effects of the vane on the clharacteristics of the revised model. -4 table of the fives presenting the results is given below: Effects of caopy and revised vertical tail on the Effects of cmopy and revised vertical tail on the Effects of cmopy ad revised vertical t

11、eil on incraental aerodynamic characteristics in pitch, p = 0 . 4 aerodynamic characteristics b- sideslip, a = Oo . 5 lcteral characteristics produced by vertical teil, a = Oo 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Variation of with hch nu

12、mber . 7 characteristics in pitch, p = 00 and it = Oo 8 characteristics in sideslip, a = Oo and it = 0 9 deflectioll for various vzlues of CL . 10 CnP Effec+,s of yaW-d83qer vane on the Eerodynamic Effects of yaw-damper-vene deflection OT? tne aerodynmic Vzriation of lateral characteristics with yaw

13、-damper-vsne S-y of yEw-dmper-vme chzrecteristics . 11 The model with the canopy and the revised vertical tail used in this investig the model withoxt the cmopy and with the original vertical tail is referred to as the original model (refs. 2 and 3j. A summary of static longitudinal and hteral stabi

14、lity character- is-kics for the various configurations without the yaw-duper vane are presented in teble IV. Experimental and estimated yaw-damper-vme characteristics are given in tcble V. DISCUSSION Effects of Cmopy and Revised Vertical Tail Aerodynamic cheracteristics in pitch.- Addition of the ca

15、nopy and revised vertical tail resulted in about 10 percent grezter ve1ues of longitudinal force for the revised model in the low lift range but did not significantly alter the lift-curve slope CL or the static longi- tudinal stability (fig. 4 and table IV). Most of the increased longi- tudinal forc

16、e and the gositive increase in lift at constant angle of attack is produced by the cmay (figs. 4 and 5 (b) ) . The lift on the canopy and the greater drag of the larger vertical tail produce more positive vahes of Cm at constent lift coefficients for the revised model, with a resulting increase in t

17、rim lilt coefficient for both velues of it. For constant angles of attack the stebilizer effectiveness was about the sane for both models (table IV) . Ah Aerodynamic ckacteristics in sideslip.- The culopy had a destabi- lizing effect on the directional-stability derivative as expected and incressed

18、the effective dihedral (fig. 5). The effect of the revised vertical tail was to increase both the directional-stability derivetive and the positive effective dihedral of the complete model (fig. 5 ad table IV). The increases in incremental lateral characteristics produced by the larger vertical tail

19、 in conjunction with the canopy (see fig. 6) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-are approximtely prosortional to the increased tail are%. The vzlue of CnP was nearer to that estimated for the complete airplane in reference 5 (fig. 7). .

20、Little change in the vaiation of the longitudinal characteristics with sideslip angle WE?S obtained for any of Zne configurations tested (fig. 5 (b) ) . It should be pointed out thzt the value of it was Oo for the revised model and 2O for the originzl model, but this snall difference should heve lit

21、tle effect on the variation of the aerodynmic character- istics with sideslip. Effects of Yaw-Damper Vane Aerodynvnic chzracteristics il? Ditch.- The yaw-damper vane produced 2 sigr-ificmt positive ircrenen-l in C, vhicn increesed with positive deflection of the vane (fig. 8), probably as a result o

22、r“ more gositive a result, trim lift coefficients also increzsed with vane deflection. The effectiveness of the vane i?l producing Cn increased greetly with increasing CL (figs. 8 zn6 lo), whereas the valrzes of C2 ad Cy for a giver_ deflection veried little with lift coefficient. pressures under “n

23、e nose end wake effects on the lirting surfaces. As Aerodynmic characteristics in sideslip.- l%e vane decreased the directional stability COB from a value of 0.002b to 0.0020 and slightly imreased the positive efrective aihedral of the model (fig. 9 md table 11). me emerinental incremertzl chmge in

24、the slope of the hterel-force coefficient-curves ACy due to the vme agreed well with the value ee-limted by the method of reference 6 (table V) . Velues OI ACzP and ACn est-ted in a similzr mer are somewhz-l low. For the rmge of siaeslip mgles irwestigEted, the changes in the values of CL, CX, uld C

25、m at a constznt vme deflection were slight. Experimental values of CyEv, CzBv, and C obtained fro= figure 10 were close to those estimated by the method of reference 7 considering the vane to be an isolated lifting surface (teble V). The mne effectzveness psrzneter P P -v C increased rapidly with in

26、creashg lift coefficient md slightly n% with smgle of sideslip (fig. 11). The dashed portion of the Ptrh curve wzs estimated by ushg e vdue of CnBV for cs = OO to extrapo- late to e vme deflection of 15O. Since the vane is not symmetrically mounted on the fuselage, a vane deflection of -bo or a ruCd

27、er dezlection of about -1.5 (ref. 3) would be required to maintain zero sideslip. The rudder wm about three times as effective as the vme In producing I . trim sideslip vlgles. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-8 NACA FU4 L54F25 CONCLUS

28、IONS A wind-tunnel investigation has been rcade with the revised 1/16- r is tne radius; all dinensions ir- inches X 0 1.000 2.000 3 I 000 4.000 5.000 6. oca 7.000 8.000 9.000 10.000 11.000 16.250 17. ooo 18. ooo 19.000 20.000 21.000 22.000 23. ooo 2b. 000 24.297 31.500 r 0 .382 -719 1.010 1.256 1.45

29、7 1. Slk 1.729 1.806 1.851 1.871 1.675 1.875 1.872 1.858 1.833 1.754 1.7k3 1.679 1.602 1.513 1.485 -780 11 . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-i p.11 Aimensions in inches I 3 -38 0 1.109 3 .kh .06 1.125 3 -75 .37 1.199 4.06 .6e 1.271 k.

30、38 1.00 1.339 4.59 1.31 1.400 .31 1.93 1.515 a6 .25 2.87 1. $1 7.50 4.12 1.780 8.44 5.06 1.835 9.36 3.9 1.870 9-70 6.32 1.871 10.39 6.62 1.879 10.31 6.93 I. 883 10.61 7.23 1.882 a Cross sections normal to plane of symnetry: At xc = 1.93 2.020 PY Upper surfwe, 22 1. log 1.146 1.371 , 1.601 1.810 1 -

31、919 2.020 2.070 2.060 2.020 1.965 1.940 1.910 1.880 1.882 At xc = 2.87 k“i 2.070 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-* c Model WL cLa Original model -.356 .047 model -0.365 0.04.( 1 Revised TADLl? IV SUMMARY OF TIE AEi7ODYNMC CIIARACTERIS

32、TICS FOR ORIGINAL AND RTiVISED MODELS (a) Complete model- 0.061 -0.018 0.425 .445 13stimtes for revised model from reference 5 I I 1 -.OU I -.0008 (b) Tail off Mode1 Original ckt CnB cyP Xmin wL model b-o.oo36 b-0.0we 5.- EfZects of c.mo)y revbed vertical tail on the aeroayl chzracteristics in sides

33、lip, a = Oo. Flagged symbols and. dashed are for original node1 (ref. 2). na-i c lines Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L54F25 21 -4 -2 0 2 4 6 8 10 P, p = 00; it = 00. Provided by IHSNot for ResaleNo reproduction or networking

34、 permitted without license from IHS-,-,-0 .I .2 .3 -4 -5 -6 .7 CL (b) C, Cz, a-d Cy against CL. Figure 8.- Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-03 .02 Cn .01 0 -.o I .I 0 CY -.I .o I -.02 Provided by IHSNot for ResaleNo reproduc

35、tion or networking permitted without license from IHS-,-,-NACA Kt4 L54F25 n 0 0 9.8 h -9.5 o Vane off Crn .08 .O 4 0 .I 0 -2 0 2 4 6 8 IO Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-28 PACA RM L5kF25 Cn 0 701 “02 v- I I I I I 0 .6 CY i j j -I .I

36、-12 -8 -4 0 4 8 12 16 Figure 10.- Variation of lcteral characteristics with yaw-daqer-vane deflection for several vaTaes of lift coefficient. p = oO; It = 0. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA RM L34F23 -2 0 2 4 6 BY deg a) Variation of Cng,with p, Q= it =Oo. 29 0 Cng, -.0002 -.0004 0 .2 .4 .6 (b) Variation of C with p= it.0: “8, 4 Btrim 0 -4 Figure 11.- Sunmary of yav-mer-vme characteristics. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-