NASA NACA-RM-L55L21-1956 A free-flight investigation of the effects of a sonic jet on the total-drag and base-pressure coefficients of a boattail body of revolution from Mach numbe.pdf

1、L Upy .RM L55L21NACARESEARCH MEMORANDUh_1,r;:jlwxwwU Wwim;,J2L gNATIONAL ADVISORY COMMITTEEFOR AERONAUTICSWASHINGTONMarch 8, 1956- ,- . . - . . . . . . . .-. -._ ., . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-rI. . . . . . . )JlGRADE OF OFF

2、JCER PLAHING WANGE) , .”,/-,- . “ “-“- I.:, -Lid. - - .-.Figure 3.- Model and booster on launcher. L-87680.1 . . . . .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-,NACA RM L55L21 13Mr.1.61.41021.0 .8.6.4 -Power-off (first coast )+ %Ouer-on+ + Powe

3、r-off (seaondooast )*.20 2 4 6 8 10 12 4 16t,aeo(a) Wdel 1.1.81.6 /- 1.4 / 1.2 1.0 .8 .6.4t Power-on Power-off (second aoast .2o 2 4t, sec(b)Wdel 2.Figure 4.- Variation of Mach number with time. . -. .Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I

4、IiIIR60W106 Model 2power-on- 5040 / Model 2“power-off/ .Model 1 /power-off .-/“30 /- Model 1power-on/20100 r.8 a719 1*O 1.1 1.2 1.3 1.4 1.5 1.6 1.7MFigure 5.- Veriation of Reynolds number with Wch number for nmlels tested.Reynolds numlmr is based on Imdy length.sIProvided by IHSNot for ResaleNo repr

5、oduction or networking permitted without license from IHS-,-,-NACARML55L21. 15%P, /(.) Total and base drag coefficients.2.82P.1.9 1.0 1.1 1.2 1.3 1.4 1.5 1.6 1.7M(b) Base-pressure coefficient. .- . .-V.8 .9Figure 6.-and jetModel 11.0 1.1 1.2 1.3 1AM(c) Jet pressure ratio.Total and basepressure ratio

6、097”4:1.5 1.6 1.7drag coefficient,base-pressure coefficient,as a function of free-streamMach number. . . ._ . . . . . _ -Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-%Figure 7.-and estnumber.a?mmmL NACA RM L55L21(a) Total d base drag coefficient

7、b) Ease-pressure coefficient.(c)Estimated jet pressure ratio.Total_and base drag coefficients,base-pressure coefficient,imated jet pressure ratio as a function of free-streamMachde2(%=0”7)”“.*Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-L NACARM

8、 L55L21 17.3.2CD.1I I #Pj() I I= 240-Tz- -= Av” &fModel1 I/ cDO / * , Rer.6d k /j 1Pj . cDm=2.07 IT/ L fP =3.700 av.d /0. .9 1.0 1.1 1.2 1.3 1A 1.5 .M 1:7.4.2c%o-. 2P,/(a) Total drag coefficient.Rd.6“” C%ofr.8 .9 1.0 1.1 1.2 1.3 14 1.5 1.6 1.7M(b) Base-pressure coefficient.L / . Rat.63 -_ - -Y - - M

9、del 2P. / . Model1 eatlmnted2 / /10.8 .9 1.0 1.1 1.2 1.3 1.4 1.5 1.6 1.7MFigure 8.-and jetbodies.(c)Jet pressure ratio.Comparison of total drag coefficients,base-pressure coefficientspressure ratios with fres-streamMch number for conical boattail5=0706. .b_ - . .+ . - -.-. - . .-Provided by IHSNot f

10、or ResaleNo reproduction or networking permitted without license from IHS-,-,-/NACA FM L55L21.3“.2c%.,.1 I(oc-.l 1 .2Pj / P.(a).3.2Cpbou.108.9(b)1.0 1.1h!1 a712 1.35Hla/ Pj/Po=3 .50Pj/Po=3.00Pj/PO=Z=501.4 1.5Figure 9.- Variation of power-on base pressure coefficientwith jet staticpressure ratio and with free-stream Mach number.mcA - Langley Field, VJ.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-