1、TEE 2 3916 An experimental in-?estigation ha6 been conducted on bodies of rev- olution in the -langley U.gh Mach number jet at Mach nt+ers of 2.37, 2.98, md 3.90 and Reynolds numbss of 0.9 X 136 to 1.37 X lo6 per inch a+ angles of attack to 90. The investigation was made to determise the effects on
2、the high-ayle aerodynmic characteristics produced by bluntiag a pointed oglvd nose to hemispherical, by ch8nging the face shape of a . cylindrical noae from concave hfor wee Gr attack to 250 :refs. 1 to 9, fcr example), but few experhentsl Investigaticns have been made En bcdies with thesp shapes at
3、 stglee of attack much above 3 or b- (refs. 10 and 111. q?lication in the design of Losilee which could be fired fm super- sonic drcr8f-t normal to *ture varied ,40m approximately no F to apprar- imstcly 30 F during each test. an average temperature of w0 P. were eting-mounted on a two-cauponent int
4、ernal strain-gage balance which MB used to meseure normal force and pitching mament. + tus-of-atteck range of wo to gOo was cwered in 15 incraente by linserting the model sting iato blocks, each of which bad a hole bored at om of the mee of attack. These blow irere mute tnc Plrat series, Identified
5、herein as cgivd. be stable for the angler, of attack af th?6 investigation. As might be expected, the noses with the convex faces (posltlve d/2r) 1. general possess greater stability aboilt the 50-percent body-lcugtii tiiu- tion thss those with the cancave Pace6 (aeegatirr, le08 pladonn area for the
6、 former fomer2 of the refereiiL momento. Specifically, :?.we 6, which preuentrj Cm plotted egdnst face shape ratio d/2r, iicwe e alight ncgat,.i * DL * . effects of variation In 8fterbsQ lenh on Cm t . fie66- rtikio-7 TIGS, a resd.t tict reconciled by the cowlueionc of referenzc 9. Thecretical Compe
7、isous 2wparisons of expcrbentd. and ttecreticd % for chree noses; reprt-dentat,ive =i the configurations of this Investigatior, are shown In figure 12 as functiomi of u. T!x thcoreticP,; Valile8 of CN %ere obtained frtm flat-plate Newtonian tbeory (2 si,12u), c?.rcular -bw Newtoclan theorj (I“ sinlo
8、n to Zircular 3odjsc . pointed cgivrrl not35 (fig. lZ!(a) are additional predictiono fiam the moClfied and unmodifieci cevtor?lan theories. Becauee thcee are eesent1aLl.y byperaonlc the les, the poor agreement betveen tbe experimental. and theoretical results in figwea 12 and 13(a) (for M 4 Also $re
9、sented in fig in figure l3(a) is ebt acr expected. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-IC. Cross-Flow ?YL Correlatior The nomal-force values ci fig-lxe J(a! h?e been referenced T;o a s-:lcw drag coefficient (ref. 1G) against the nxmd Mach
10、 number. Tnis CC,USE eli the data to csLia26e i.Zt0 mwe si? less 3Le curve, still in qTeercent with Nek-tmis? theory fcr XN 3.5 or 4. ia approximately constarit dsc for It my be worth noting that the exgeraentd CgPc 3.3 or 4. it is inte .sting tc ,iote that the ci-oss-fl- drag correlation and the Ne
11、wtonitxi tkeory are similar j.n that they ere both bn 96. (NOTs 551) U.S. Naval Ord. Test Station, Inyokern (China Me, Calif.), reh. 12, 131. NAVGRD Rep. 1281 9. Smith, Frer? K.: A Wind-Furmel InvestiEation of Effects of Nose Blunt- ness, Face Shape, and kfterbody Inngth on t2e Aerodynamic Character
12、- istics of Bodies 3f Revolution at Mach Nmbers of 2.37, 2.98, and 3.90. NASA IM X-250, 1960,. 10. leniand, Jim A.; Aerodynem:c Characteristics of a CirClt- Cyiinder IIACA m 3%1? at Mach #umber. 6.06 and Angle6 of Attack Up to 90. i957. (Supersede6 NACA RM L54A14.) Provided by IHSNot for ResaleNo re
13、production or networking permitted without license from IHS-,-,-11. ijriqdle, C. Carl: LongiLuciinal Chivacteristics at Supersonic Speeas of 2 Winged z?d a nlir*i;leso O.-Scale Half Mcdel Sparrow I Missile at Angles of Attack Vr; :o 1m“. Modi. Fssin, Navy Wpt., Dec. l?5-. -4erc 2ep. 931, David W. Ta
14、ylo?. J2. Grjnminger, G., Williams, E. P., nr,d Youcg, G. 5. 2.: Lift, on Inciined Bodies or Eievoht,ior. in Hypersonic Fiow . Jour. Aero. Sci. , vol. i7, 1i3 11, NOY. 1952, ?p. 673-69. 15. PS Reszmch Stzff: Equations, Tables, and Charts for Conpressible L Flow. N4C.4 Rer, Li.;, 135;. (Supersedes NA
15、CA TN lJ+.2?1) 9 3 14. HRiney, Eiobert h.: LJrking Charts for Rapid Prediction of Force and 5 Preswre Coefficients on Arbitrery Bodies of ?.evol%ition by Use of Newtonian Ccmcopts. NASA Tit D-176, 1959. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,
16、-i4 PIN- i Nmp R (a) Ogival noaes. Figure 1.- Geometric characteristics of the del cusnponent8. Dimension h Inchef. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. P- z I i t I 0 )5: QD w c 6 u L I tn 3 Z z .I E k a z N n r- d 88888 1 B -i- o Provi
17、ded by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.,. . 9,. , . .D . . Afterbodies . Figure 1.- Concluded. t Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-24 E- d 8 E 0 9 k 0 I Provided by IHSNot for Resal
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