NASA NACA-ACR-L5H08-1945 Supersonic-tunnel tests of projectiles in Germany and Italy《德国和意大利投射物的超音速风洞试验》.pdf

1、NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS IGlWLLY ISSUED October 1945 a8 Advance -Report 508 SupwsONIC- TESTS OF PROJECTIIES IN (zemwvr m ITALY By Antonio Ferrl Langley Memorial Aeronautical Laboratory hngley Field, Va. WASHINGTON NACA WARTIME REPORTS are reprints of papers originally issued to pr

2、ovide rapid distribution of E I- advance research results to an authorized group requiring them for the war effort. They were pre- viously held under a security status but are now unclassified. Some of these reports were not tech- nically edited. All have been reproduced without change in order to e

3、xpedite general distribution. L - 15s ., Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Eg Antoni.0 Ferri Tests 1.vere :erfolorned in th4 Gbtti-Y?gcn (Gerrxang) and C;iA.donia (Italy) sqeyscnic turmels in orde;. to deter;nine the zsociynm.ic chzrhct

4、eristics of Trojectiles of varios shqes. for the Gotthgen tests snd fron l.h$ to 2.66 for the Gufdonfa tests. The results show thst increasing the relztf-ve length of the nose c?.uses the drag coefficient to decresse i:f*s the varl .ttiail of the drzg. Co(3f- Existinq aerodplsmic theory gives velues

5、 of the Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Force tests of snall models 0.393 inch in diameter were concluctt3d in a supersonic tarriel hayiing: a test section aDzroximately 2.36 by 2.84 inches, The shape of the models vas systematically

6、varied to determine the effects on the aerod7pmic chayacteristics of: (1) Nose profile shape for B typical fineness ratio (2) Nose length for noses with circular-arc profiles (3) Smell tsper of tke tpil of the projectile The program carried out at the Guidonia Laboratory had as its aim the developme

7、nt of BT? optimum sha;?e for a l.El2-inch-caliber mtitmk projectile. Becmse of the relscivelg 1YrFe size or“ the test nodel, it was possible to obtain pressure-distribution studies as well as precise ae:rcJdynmic dats for comparison with results dcrived by exist ins theory. shprp-nose zrojestilss at

8、 ACTO anii;lc. of attack and the thecries of refercnces 7 and 8 for bodies of revolution at ari angle of yaw in:ere used to ccmpuG5 the theor2tical characzeristtcs of the varioxs conical riosss for coni- narison crith the experinental rzsults. The asrodynarric thcorg cf ninlnwn-drzc pro jactiles Tre

9、sentcd In r?fl-“r- enzes 3 snd 5 to 7 was used as s guide in tha design of the vzrious nose shspas cf ths projectilzs testad. The theories 1;resenLed ir, refsreilces 1 to 6 for The syrnbols used for defining the aerodynamic coef- ficients aid the gsometric charactzrfstics of the pro- jectil3s em giv

10、en in figurs 1. sgeed of sound in free stream f ree-s tre sm ve lcc i ty free-strean Mach number (Vo/a,) free - s tre rm dyn srni c pres sure locel static pressare Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-11 /P - Po nressure ccsfficient ( 90 :

11、 dimietep of body of projectile i-esultmt force on projectile dr 2 g lrif t pitching moment about rear face of projectile -:3itchins-moment coefficient sbout reFr face of 3 lmptr?_ of proJec tile raifu3 of nose of proj2ctfla cent er -of - prz s sure pcs i ti on, iaie as1x.e c? fr cn ye Rr face of po

12、ject1.le =isle of attack of projectilz Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 Ain2-Tmnel mid 3xljeri:nm.t a1 Methods Te s t Yode Is The models each had a diweIer of 0.593 inch ?rid ders siryported b; i! stilng atrzched to the rem face. The

13、 ainiensioris of tm sting end the tare systern adopted we not OVJTI. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NdCA AC3 No. LSHO8 5 I I* were of circular Frofiie witn the isedii T arying from 6.51 to a, (conica1 nose). POP the nose with 6.31 ra

14、dius (model 1, fig. 3), the end of the ncse WFS tangefit to the cylinder Pt their jmctare bat, for the other models, the profllf of the nose terrzinated xith I its tangent -inclined a+, an angle E with respect to the t generatrix of the cylinder. Length of the ncse.- Five models having Rose lengths

15、fic. I+) were tested to detee-mine the eiiect of thc lensth of the riose. The nsses of all the mcdels had circular profiles tangent to thz cylinder forming thr: body of the projectile. I varyhg from G.FdV5d (models 5, 6, I, 7, and 8, Tafl tapr.- Threa mcdeis derived from model 1 snd havin,thrl3e dif

16、fercnt tpil tnpsrs (iiiodzls 3, 10, ana 11, fig. 5) were testjsd to determirAe tiia zfffect of tail ts,3er. Wind.-f,urinel tests. - The restllts of the exneriments at thz ers (fig. 21). The differences in drrg coefficients were not 1sry. The o tiler aerody:? mi c ch er ac te ri s tics 1:iere not qli

17、pre ci 25 ly altered. Tlie drsg coefficient for 2 given projectile shepe dacressed 5s the Xach n:Jmber wzs increased. This effect WRP most pronounced at the lower sui.:;ersonic velocities ; the varic“tion Ft lilech nw-beys or tile or2er of 5.0 WES clrimge -. z;?prcc1 sbly with angle of attack. In th

18、e lowar suntrsonic velocity rmge the center GP Fressure moved tosvzrd the i“eEr of the projectile ,FS the spaed was highsr Lech rlmSe.rs. sli,.-ht. 7- -L e yosition of the cefi-ter oi“ pressure dld :lot incw vGacl qm . bit tended to epoach R fixed. loctiox at the 1 2 7 i I I o.:o .56 G.29 .28 . “3 .

19、2b The projectiles used in the firing tests had sn zggl-5 or sttack ci riesrly 3O 2nd 2. Inour:?:iet, ring. Drag coefiicimts obtained f?om firfng tests zt argles of atthr,t were i=c;uiv- lent to 9 wind-tunnel angle of attsck of ebout 7.5O. The differences theref3z.e can!-:ot be entirely dze to the p

20、resence of khe Sourrelet nor to ch9 3rTor in mgle 0.f atisck. The differences may probzb1-y be attributed in 2,art to the difference or surface ifnish betweeri the tirnnel rfiodsl snd the fired projectiles, the rotstion of tl? fkGd grojactile about its axPs, and the c?ifr7ohind the blmt feca cf the

21、nose 8 ra.7i.d expmsion GCCUIS, and the ?ressilres a short distonce from the n3se beconie lowe:. l;hs,ii for ths conica.1 nose. Thsss 1ow.r pressures act owl- E ralst1s.el.y large part of the rrorital erea of the projectile; consoquantly, a lower drc.g coefficfent is obtained for the blunt nose thmi

22、 for the cmical nose. The pressure 011 the rear face of the ;?rojectile is about the sane for both types of nose. Tho lift at the same angle of tta.ck for the blunt noses is slightly r,Sreater than for the conical ncses, and the cen-cer or“ .pressure is tnerefors imther fDrvisr4. These differeaces a

23、re vary scail, nojll;ve. It xry he mentfonsd thst th.e blunt type or n3se is Mors prrctical than tdhs sherg-,pointed nos6 from the stand7cints of con- s trinction md nzin tanmcu. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-12 2, The drgg coelfici

24、eric for c7 given nrojectile shsp3 decreases as tkLs Xach numbel- is incrassed. This effect is most pronounced at the 1ov:eP sinersonic velocities; the variatfon at Mcn riwvhers of Lhe ordc.r of 3.0 is slight. Lmgley TIemori 21 A3ficn rut ic al Itsboxantory Natfonal Advisory Cormittee Tor Asrcnputic

25、s LaDg! e y Fi e Id, Ve . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. 1. Tsylor, G. I., end hiscoll, J. Vi.: Tile Air Pressum cn a Cor,$ XovIng et EiSh S;)esd?. PYOC. Roy. SOC. (London), ser. A, vol. 157, no. 838, mb. 1, 1953, I pl=. 278-311. c

26、 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-8. I I- C q -. ., Projectile . - 1,. x 2, 0 25 40 1.00 2.00 5.00 5.m 10 00 20.3i) 3c 00 l+o. 00 5C.03

27、 60.00 70.00 80. 00 gc.00 lU0 00 16 51 j 0 10 - . .-+ I .1 j .6 .Li I -9 .L! i i 1.6 1.3 2.9 1.4 i 1;.1 2.2 ; 5.7 3.3 j 8.9 7.5 I 14.0 10.9 lb. I 17.1 19 7 21.5 24.2 27.0 li .? 2G. 7 22.5 25.e 21+. 5 2k.9 25.0 25.0 25.0 I i 7i i9 I I 0 2.5 2.7 3.2 2: 70 io: 9:; 19. 17*& 12.5 15.1 21.5 23.0 2Li. 2 25

28、.0 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA ACR No. L5H08 I I Q I i Fig. 1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 2 NACA ACR No. L5H08 I 8 I r-i a, c c 7 4 0 .cl c 0 m L4 a,

29、a 7 m c. a, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA ACR No. L5H08 _._._1_ Fig. 3 NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS Model 1 Model 2 Model 3 b f Model 4 Figure 3.- i4ouels tested at Gottirlgen to determine the nose of minimum dra

30、g. d = 0.8393 inch. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 4 NACA ACR No. L5H08 Model 5 Model 6 Mode/ 1 Model 7 NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS 1 I I - I I- 4 Model 6 b t I 6.06 - Model 6 .LTT Models tested at Gottingen to o

31、f nose length. d = 0.393 determine inch. the effect Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA ACR NO. L5H08 Fig. 5 Model I Model 9 Model II NATIONAL ADVISORY COMMITTEE Foll AERONAUTICS c -0 -I- - - c- 2.5d 5 “43 Figure 5.- Models tested at

32、 Gottingen to determine the effect of tail taper. d - 0.393 inch. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 6 NACA ACR No. L5H08 Much number, M, Figure 6.- Lift, drag, and moment coefficients and position of center of pressure as functions

33、 of Mach number for various angles of attack. Model 1. (Gottingen). Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA ACR No. L5H08 Fig. 6 Conc. . 9, 0 b 2.0 Figure 6.- Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitte

34、d without license from IHS-,-,-Fig. 7 .6 .4 .z 0 NACA ACR NO. L5H08 Much number, M. Figure 7.- Lift, drag, and moment coefficients and position of center of pressure as functions of Mach number for various angles of attack. Model 2. (Gottingenl. Provided by IHSNot for ResaleNo reproduction or networ

35、king permitted without license from IHS-,-,-NACA ACR NO. L5H08 Fig. 7 Conc. J. 6 3.2 2. 6 2.4 2.0 Mach number, M, Figure 7. - Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA ACR No. L5H08 Fig. 8 .6 A 0 Much number, Mo re 8.- Lift, dra

36、g, and moment coefficients and f center of pressure as functions of Mach numbe arious angles of attack. Model 3. (Gottingen) c position r for Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I. . NACA ACR NO. L5H08 2.0 1.6 /-2 -6 R 3.6 Fig. 8 Conc. 4

37、Much number, No Figure 8. - Concluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 9 NACA ACR No. L5H08 c .6 tF .2 0 -6 .4 .L 0 Much number, MO Figure 9. - Lift, drag, and moment coefficients and position of center of pressure as functions o

38、f Mach number for various angles of attack. Model 4. (Gottingen) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA ACR NO. L5H08 1, 1.6 1.2 -8 .4 Fig. 9 Conc. NATIONAL ADVISORY COnMllTEE Fo(l AERONAUTKS 2.8 2.4 2.0 I 4 Much number, M0 Figure 9.- C

39、oncluded. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 10 NACA ACR No. L5H08 .6 .4 .z 0 .05 dlr 0 COMMITTEE FOR AERONAUTICS I . /o . /5 Figure 10.- Lift, drag, and moment coefficients and positi0.n of center of pressure as functions of the ratio of the diameter of the body of the projectile to the radius of the nose of the projectile for various angles of attack. Mo - 2.0. (Gottingen) Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-