1、COPY 2JIRM E51Cd6.- . . -4. - -.= -* -,. .-=N were analytically resolved intollft and drag components. Pitching moment was measured about station 45and is presented in coefficient form.The qerhental results obtained for the models of fineness ratio14.2 at Mach nmibers 1.50 and 1.60 are subject to th
2、e effects of modelnose shock reflecting fr.gmthe tunnel walls into the vicinity of thebase. For the models of fineness ratio 12.2 at the free-streamMach num-ber of 1.50, it was ected that the reflected shock intersected thesting downstream of the model base but the base pressure might st be -affecte
3、d Qs indicated in ref=ence 5. For all models, however, the effecton the force coefficients other then the base drag coefficientwas pre-sumed to be comparatively small.The data at a free-streamMach nrmiber1.50 for models of fInenessratio 14.2 and 12.2 and the data at a free-streamMach number of 1.60f
4、or nmdels of ffneness ratio 14.2 were probably affected by weak disturb-ances in the flow (reference3). Due to the lack of pressure instru-mentation no ccmrection to the data could be evaluated. Howev=, theprobable magnitude of the .327 “-5p 1.WO 4.Anglea. attU&.l0(e) F*OS ratio,12.2. :.2lo. D.1ani-
5、sa 1.E43 1.70 1.s0 1.90 2.00.-.Free-strum Mech ntmberj Q(f) Fineneseratio,14.2. : . -.Figure 7. - concluded.2ffeetof boattiog on c c_ec-tareeticaof - MS inveetlgated.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACARM E51C06 29.4a71Angle of attac
6、k, (dig)-*- 86.2 e (a) Idft ctx$fickrt.II -lWA m-lo (referenae3) o:% IZ.2 0.3671 12.2 .367.12 8 -. -L 1b 0- ti- -L.08“ a4 - . -,.04t - -z .unO* r 1(b)Pl Dmnellteoeffmtent.8- 1.40 1.30 1.66 1.70 1.80 1.90 2.00Free-streamMachmmba?,(c)Incrementoffore drag coefficient.Figure 8. - ?Hfect of boattail convergence on aerdmmic -acterl.ettcs . “Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
