AOUSW TECHNICAL. LIBRARY. 79- t u68 [VERSITY OF TEXAS AT AUSTIN

Size: px

Start display at page:

Download "AOUSW TECHNICAL. LIBRARY. 79- t u68 [VERSITY OF TEXAS AT AUSTIN"

Phyllis Benson
5 years ago
Views:

Sutter Aerspace Engineering Reprt 79002 This wrk was supprted by the U.S. Army Missile

1 Mmshk* AUSW 79- t u68 [VERSITY F TEXAS AT AUSTIN THE EFFECT F A CMPLETE SPIN TURBINE N THE EXHAUST FLW-FIELD FR A TUBE-LAUNCHED RCKET TECHNICAL. LIBRARY Samuel J. Sutter Aerspace Engineering Reprt This wrk was supprted by the U.S. Army Missile Cmmand thrugh cntract DAAK40-77-C-0131 January 1979 Department f Aerspace Engineering and Engineering Mechanics

SECURITY CLASSIFICATIN F THIS PAGE (When Data Entered) I. REPRT NUMBER AER 79002 REPRT DCUMENTATIN PAGE 4.

TYPE F REPRT & PERID CVERED Final, Jul 77 thru Sep 78 6. PERFRMING RG. REPRT NUMBER 7. AUTHRfsJ 8. CNTRACT R GRANT NUMBERfB.) Samuel J. Sutter 9.

2 SECURITY CLASSIFICATIN F THIS PAGE (When Data Entered) I. REPRT NUMBER AER REPRT DCUMENTATIN PAGE 4. TITLE (and Subtitle) The Effect f a Cmplete Spin Turbine n the Exhaust Flw-Field Fr a Tube-Launched Rcket READ INSTRUCTINS BEFRE CMPLETING FRM 2. GVT ACCESSIN N. 3. RECIPIENT'S CATALG NUMBER 5. TYPE F REPRT & PERID CVERED Final, Jul 77 thru Sep PERFRMING RG. REPRT NUMBER 7. AUTHRfsJ 8. CNTRACT R GRANT NUMBERfB.) Samuel J. Sutter 9. PERFRMING RGANIZATIN NAME AND ADDRESS The University f Texas at Austin Dept f Aerspace Engineering & Engineering Mechanics - Austin, Texas It. CNTRLLING FFICE NAME AND ADDRESS Cmmander, US Army Missile R&D Cmmand ATTN: DRDMI-TI Redstne Arsenal. AL MNITRING AGENCY NAME ft ADDRESSCif d/zfrenf frm Cntrlling lllce) Cmmander, US Army Missile R&D Cmmand ATTN: DRDKI-TLH Redstne Arsenal, AL DAAK40-77-C PRGRAM ELEMENT, PRJECT, TASK ^AREA 4 WRK UNIT NUMBERS DD Frm REPRT DATE Jan NUMBER F PAGES 31 IS. UC SECURITY CLASS, (l thla reprt) 15«. DECLASSIFI CATIN/DWN GRADING SCHEDULE 16. DISTRIBUTIN STATEMENT (f thla Reprt) Apprved fr public release; Distributin unlimited 17. DISTRIBUTIN STATEMENT (l the abetract entered In Blck 20, If different frm Reprt) 18. SUPPLEMENTARY NTES The findings f this reprt are nt t be cnstrued as an fficial Department f the Army psitin unless s designated by ther authrized dcuments. 19. KEY WRDS (Cntinue n reverse aide it necessary and identity by blck number) Spin vanes Spin turbine Exhaust plume Tube launcher Fluid flw Rcket launcher 20. ABSTRACT (XTntbiue n. nvermm nidn if rmce^aary and identify by blck number) Unbalanced frces n tube launched rckets during launch caused by exhaust fluid flw in the launcher-rcket annular gap is a prblem cnfrnting tube-launched rcket system designers. ne alternative cnsidered t alleviate the adverse effects is t rtate the rcket abut its center f gravity during the launch phase t average ut small deviatins in the flight path. The spin turbine is a pssible alternative with which t increase the rcket's angular mmentum. Previus wrk cnsidered a single vane's effect n the exhaust flw, a cmplete DD» j^trj 1473 EDITIN F» NV S5 IS BSLETE SECURITY CLASSIFICATIN F THIS PAGE (When Data Entered)

$mree it) :.)-;. i.: i H T* '' V< ^zn-.).'. ':- -fy^ -»-> ' -l.: 1-. >.: r,,, : : ; I II' ' ' ^. -<' T '( '." ", -) ' : '{ : ' ;; lyt '^ ;;":. f.v ' v ' w,.,-,..,- r _,.,+ < ( ;. V^v -;.>-,..-, -,-.$

3 SECURITY CLASSIFICATIN F THIS PAGEfWhan Data Entered) 20. ABSTRACT Cntinued... spin turbine effect n the exhaust flw, and a rcket nzzle equipped with a cmplete spin turbine exhausting int a cylindrical launch tube. The current prgram demnstrates a significant difference in the flw arund an islated single vane frm that arund a single vane f a cmplete spin turbine. Three vane heights are cnsidered.».ufuine. mree it) :.)-;. i.: i H T* '' V< ^zn-.).'. ':- -fy^ -»-> ' -l.: 1-. >.: r,,, : : ; I II' ' ' ^. -<' T '( '." ", -) ' : '{ : ' ;; lyt '^ ;;":. f.v ' v ' w,.,-,..,- r _,.,+ < ( ;. V^v -;.>-,..-, -,-.- " -."(.-, ". '' '' >!if>rr ; T v-'i:' ] ' (br'-fn. - ) v" - ^-- V-:'" -^r?.;vm"-.ri?< ' : ' '' / -w, j.-, -,,. *,,,,.,.; - ; -' : :-> ;- ; : :' -. :. ', :-;-., v/j. :....,.,.'.,. n,, r - drt-^ SECURITY CLASSIFICATIN F THIS PAGEfVfTiBn Da(a Bnfred,-

4 » The Effect f a Cmplete Spin Turbine n the Exhaust k Flw-field fr a Tube-Launched Rcket by Samuel J. Sutter, Jr. Aerspace Engineering Reprt *This wrk was supprted by the U.S. Army Missile Cmmand thrugh Cntract DAAK C-0131 Department f Aerspace Engineering and Engineering Mechanics The University f Texas at Austin January 1979

5 TABLE F CNTENTS Page INTRDUCTIN 1 EXPERIMENTAL PRGRAM TEST FACILITY 2 Cmplete Spin Turbine 2 Test Prgram 3 DISCUSSIN F RESULTS 4 Cncluding Remarks 6 REFERENCES 7

INTRDUCTIN At present, the prblem f unbalanced frces n the rcket caused by fluid flw in the launcher-rcket annular gap cnfrnts the designers f tube-launched rcket systems.

6 INTRDUCTIN At present, the prblem f unbalanced frces n the rcket caused by fluid flw in the launcher-rcket annular gap cnfrnts the designers f tube-launched rcket systems. ne alternative under cnsideratin t alleviate adverse flw effects is t rtate the rcket abut its center f gravity during the initial launch phase in rder t average ut small deviatins in the flight path. A spin turbine is a feasible alternative with which t increase the rcket's angular mmentum. "The Effects f Spin Vanes n the Exhaust Flw-Field fr a Tube-launched Rcket" (Ref. 1) reprted n the spin turbine applicatin. That prgram investigated the single vane's effect n the exhaust flw, the cmplete spin turbine's effect n the exhaust flw, and a rcket nzzle equipped with a cmplete spin turbine exhausting int a cylindrical launch tube. Cntinued interest tn this area prmpted additinal experimentatin; particularly cncerning the shck/viscus interactin generated by flw arund adjacent vanes and the effect f vane height, h, n the exhaust flw thrugh the cmplete spin turbine. The current prgram demnstrates a significant difference in the flw arund an islated single vane frm that arund a single vane f a cmplete spin turbine. This interactin is shwn fr three vane heights in the fllwing sectins. 1

EXPERIMENTAL PRGRAM TEST FACILITY Similar experimental prcedures as detailed in Reference 1 were used in this fllw-n prgram. The blw-dwn type facility. Figure 1 was used t generate and recrd the data.

This same rcket nzzle was equipped with a cmplete spin turbine similar t that shwn in Figure 3. In rder t btain apprpriate data, the spin turbine was instrumented as shwn in Figure 4.

7 EXPERIMENTAL PRGRAM TEST FACILITY Similar experimental prcedures as detailed in Reference 1 were used in this fllw-n prgram. The blw-dwn type facility. Figure 1 was used t generate and recrd the data. Figure 2 presents the flw exhausting frm a reservir where P., = 6.74 x 10 N/m (978 psia) thrugh a 10 cnical nzzle and int quiescent air. This same rcket nzzle was equipped with a cmplete spin turbine similar t that shwn in Figure 3. In rder t btain apprpriate data, the spin turbine was instrumented as shwn in Figure 4. In additin, data were btained utilizing supersnic pitt-tubes as pr- trayed in Figure 5. The three stagnatin pressures investigated fr each vane height are listed belw: 2 P tl N/m (psia) 6.87 x 10 6 (987.9) 5.09 x 10 6 (738.4) 3.44 x 10 6 (499.2) Cmplete Spin Turbine The gemetry f the large vanes, h v = cm (.205 in) used in the cmplete spin turbine were identical t that f the single vane used in Reference 1. The dimensins are reiterated in Figure 6, 7a, and 7b in this reprt. Nte that the cmplete spin turbine used in tests f Reference 1 had vanes with a thickness f cm

(.030 in). Hwever, t facilitate instrumentatin f the cmplete turbine the vane thickness was increased t 0.127 cm (.050 in) in the current prgram.

8 (.030 in). Hwever, t facilitate instrumentatin f the cmplete turbine the vane thickness was increased t cm (.050 in) in the current prgram. Further the vane heights were nt cnsistent frm Reference 1 t this prgram. The table belw presents the differences: Reference 1 Present Reprt Vane Height cm(in) Vane Height cm(in) VI (0.205) Vll (0.205) V (0.137) V (0.155) V (0.068) V (0.105) Test Prgram The effects f the cmplete spin turbine n the free exhaust were investigated in this prgram. Use f the launch tube and the cnsequentially cnstrained plume flw field were nt examined during this cntinued experimentatin.

DISCUSSIN F RESULTS The flw field f a cmplete spin turbine is very cmplex. The relatively "clean" plume in Figure 2 is radically changed by the additin f the turbine t the exit f the nzzle.

In rder t btain sme measure f the decrease f ttal pressure within the exhaust plume, the pitt-pressure prfiles were integrated ver the cntrl area A ne at each x statin dwnstream f the nzzle.

9 DISCUSSIN F RESULTS The flw field f a cmplete spin turbine is very cmplex. The relatively "clean" plume in Figure 2 is radically changed by the additin f the turbine t the exit f the nzzle. The phtgraphs n Figure 8 are repeated frm Reference 1. They demnstrate the cmpund effects f the interactin flw f ten spin vanes cmprising the turbine. In rder t btain sme measure f the decrease f ttal pressure within the exhaust plume, the pitt-pressure prfiles were integrated ver the cntrl area A ne at each x statin dwnstream f the nzzle. The integral pit _ Ptl ne r ne ne was evaluated with a trapezidal apprximatin. The average pi tt-pressures, nndimensinalized by dividing by p., = 6.87 x 10 N/m (978 psia), are presented in Figure 9. The triangular symbls have been added t Figure 27 f Reference 1 t demnstrate the effect f spin height, h, and thickness n the dwnstream flw field. The clse agreement between the values fr the V3 turbine and fr "n spin turbine" indicate that the V3 turbine causes little net lss f ttal pressure. The average values fr the pi tt pressures measured dwnstream f the VI1 turbine were significantly lwer than thse fr the V3 turbine. Recall that the vane thickness

This ttal pressure lss due t a spin turbine in the exhaust shuld significantly alter the flw field in a launch tube, where the stagnatin pressure f the exhaust is a critical factr in the generatin f

10 fr the spin turbine f the present test prgram is seventy percent greater than fr the previus test prgram. f imprtance t the spin turbine designer is the significant effect that the increased vane height and thickness had in decreasing the nndimensinalized pitt pressures. This ttal pressure lss due t a spin turbine in the exhaust shuld significantly alter the flw field in a launch tube, where the stagnatin pressure f the exhaust is a critical factr in the generatin f blw-by flw. Lgically, then, a spin vane can be designed which des nt significantly effect the plume lcal stagnatin pressures but is adequate in imparting increased angular mmentum t the rcket. The flw field arund a single islated vane is thrughly described in Reference 1. Figures 10 and 11 present idealized flw and the shck wave structure prduced by a single vane fr M = The flw field arund a single vane in the cmplete spin turbine shws signficant effect frm the shck structure f the adjacent vanes. Figure 12 shws that the peak static pressures ccur cnsiderably further dwnstream f the leading edge as cmpared t thse fr the islated vane. Nte the increase in the lcal surface pressure and the aft mvement f the peak is attributed t the impingement f the shck generated by the adjacent vane. The static pressure distributins n the turbine surface between the vanes are presented in Figure 13. These data are repeated in Figure 14 f this reprt, which includes the data fr the islated vane (as taken frm Figure 16 f Reference 1). Frm the data presented in Figure 14, it is clear that Figure 21 f Reference 1 des nt clearly illustrate the degree f interactin f the calesced shck structure. The theretical flw angles frm Fig. 11 are verlayed n the cmplete spin turbine in Figure 15. The result is Figure 16 which shws a greater degree f shck interactin between adjacent vanes than

Cnsistent with the results f Figure 9, the flw field f the cmplete turbine equipped with small vanes, h = 0.267 cm (0.

11 was presented in Reference 1. The mutual effect f adjacent vanes presented in Figure 12 is again shwn n Figure 17. Hwever, the data presented in this figure illustrate the effect f vane height. Cnsistent with the results f Figure 9, the flw field f the cmplete turbine equipped with small vanes, h = cm (0.105 in), demnstrates small adjacent vane shck interactins. Cncluding Remarks The flw arund a spin vane in a cmplete spin turbine is radically different frm that f an islated vane. Nevertheless, the disturbances can be minimized by decreasing the vane size cnsistent with that f maintaining minimum surface area needed t prduce the desired rcket angular velcities.

12 REFERENCES 1. Cribbs, D.W. and Bertin, J.J." "The Effects f Spin Vanes n the Exhaust Flw-Field fr a Tube-Launched Rcket," Aerspace Engineering Reprt 77006, December 1977, The University f Texas at Austin.

13 > > 4-> ) lira 0) s- > (-> I c t > c_> U=(» S- ) t. tn k c (/> ra Q_ u!-> t +-> J3 1-3 Q. 4-> (^ S- I/) t CD S- CL E :* Blast fleet Q) 01 t 3 t ) ai in c X 4-> r 01 S- > A 0) " l J- 3 re re 00 i~ 0) +J c c re.

14 Figure 2. - Schlieren phtgraph f the flw exhausting frm the rcket nzzle with n spin turbine. P tl = 6.74 x i 6 N/m 2 (978 psia)

15 N N M S- 01 t c: i 4-> Q > H- -C Q. (0 s_ CD +-> -C Q- I S-

16 Figure 4. - The instrumented cmplete spin tubine

17 4-1 IS) cu u 0) C (71 ) t t- +J >i P 4J r r j Q. f u M- (0 Ll_ Q. (7) 3 +-> CU u c cu M- cu

18 3 u c: C C

Nte: M ne 0.368 (0.145) 0.241 (0.095) _1_ -&- & lee side j 0.051 ](0.020) dimensins in centimeters (inches) I -^-. 0.521 (0.205) f 0.376 (0.

19 Nte: M ne (0.145) (0.095) _1_ -&- & lee side j ](0.020) dimensins in centimeters (inches) I -^ (0.205) f (0.148) T (0.083) tp view (0.031) ) Figure 7. - Detailed sketch f vane illustrating static pressure ri f i ces Scale: ten times actual size.

0.521 ~f (0.205) 0.368 (0.145) M ne $._--. (&._. i I -t-^-- I 0.051 (0.020) T 0.229 (0.

20 0.521 ~f (0.205) (0.145) M ne $._--. (&._. i I -t-^-- I (0.020) T (0.090) A windward side Nte: dimensins in centimeters (inches) M, ne (0.040) 0.11 ( L (0.050) r tp view (b) 25 Windward Side Figure 7. - Cncluded.

Figure 3. - Scilieren phtgraphs f the flw exhaustirg thrugh -h2 VI turbine, h = 0.521 cm (0.

21 Figure 3. - Scilieren phtgraphs f the flw exhaustirg thrugh -h2 VI turbine, h = cm (0.205 in), fr tw different rientatins f the spin turbine (90 apart) P tl :: 10 6 N/m 2 (978 psid)

22 A Vll turbine, h v = cm (0.205 in) N spin turbine V3 turbine, h v = cm (0.068 in) pit 5 t Figure 9. - Average values f the pi tt pressure as a functin f distance dwnstream f the nzzle. p tl = 6.74 x 10 6 N/m 2 (978 psia) ne

24 M ne = 2.34 h = 1-25 (a) weak blique shck, windward surface. M = 2.34 ne (b) Prandtl-Meyer expansin, leeward surface. Figure Simplified mdel f the flw field arund an islated vane.

p, N/m (psia) pen Symbls - single vane D 6.67 x 10 6 (987.2) filled symbls - cmplete turbine 6.81 x 10 6 (968.1).. ft, / n. nt.. x v "u 0-521 cm (0.205 in.) ^5.09 x 10 6 (738.4) A 3.44 x 10 6 (499.

25 p, N/m (psia) pen Symbls - single vane D 6.67 x 10 6 (987.2) filled symbls - cmplete turbine 6.81 x 10 6 (968.1).. ft, / n. nt.. x v "u cm (0.205 in.) ^5.09 x 10 6 (738.4) A 3.44 x 10 6 (499.2) Nte: Flagged symbls indicate repeated data, T 'tl asss i 0.1 i 0.2 i i 0.3 ' 0.4 s ne (a) windward surface 1 I " Figure Static pressure measurements n the surface f the spin vane as a functin f the chrdwise distance frm the leading edge.

P tl N/m (psia) 6.67 x T 6 (987.2) 6.81 x 10 6 (968.1) 0 5.09 x 10 6 (738.4),6 A 3.44 x 10 u (449.

26 P tl N/m (psia) 6.67 x T 6 (987.2) 6.81 x 10 6 (968.1) x 10 6 (738.4),6 A 3.44 x 10 u (449.2) pen symbls filled symbls Nte: Flagged symbls indicate repeated data T h v = cm (0.205 in) - single vane - cmplete turbine _ T2 _ ne (b) Leeward surface Figure Cncluded

CM CM ID s- > t n (-> (T3 X) t. u 01 u 1+- S- 0 5 cn ^1 ^2 5 m s JE g t C 2 CM + Q- 00 4-> <U ^ Q- E.

27 CM CM ID s- > t n (-> (T3 X) t. u 01 u 1+- S- 0 5 cn ^1 ^2 5 m s JE g t C 2 CM + Q > N c 1 (/I,,- ( 3 f -(-> 4-0 i- r 3 c C E ^ 1 ^. Nl +-> ( N r- UD (/> C CT> D. C -C r-- r~. -l-> cn ^^ c 0 CM "m E r U >«, *-» 2: Q. VD Q. ^ v f^ ^ c X C r s- tn * Z3 r-^ U1 J t UD 0 II Q. E pmi 0 +J 1 CL +-> 1 r CM +J CD C T3 M *r- II ^ x:' a c ^ * * * in c E 1 c: T3 1 C -Q 3 ^ -M CTi r H M a. J I CM I l

$r C <v C i JQ S- 3 4-> c I CL n J 4-) <D r CL CM E u IS) *-> en c a %- a a> c > t-> CNJ ^ 0 C g ^^ CVJ s B + C\J 00 Q.$

28 r C <v C i JQ S- 3 4-> c I CL n J 4-) <D r CL CM E u IS) *-> en c a %- a a> c > t-> CNJ ^ 0 C g ^^ CVJ s B + C\J 00 Q. C WD II 4-> <D +J c r " a> 10 M- S- CD rs M 00 r t J ^ P M ( N c Z3 -l-> u n3 0) x: 00 4-) C i -t-> LD 4J ai CL ^^^ r-. CL tk,, t cr. 5 ii 00 IT) I J F rsi rr-~ ^t- 10 en c n l^ c II J E I ) cn Q.

$0) +-> E 0) ^: U LD -t-> en J 4- t +-> C ) +-> r r - s- u ) "3 M- %. 00 C\J m r Q.$

29 0) +-> E 0) ^: U LD -t-> en J 4- t +-> C ) +-> r r - s- u ) "3 M- %. 00 C\J m r Q. C ii Nl -M CL Q- E *» i t J LD t- 3 i t IS) l ) * ^ N S- r Q- s 00 I r p-^ re -l-> UD 3 re C\J -M t-> t re " II C f -E r-, M re ^. E U tn *. > en 1 00 r*. E E r r- - ja E s- re 3 2: +-> Ul C 0} 3>

$3 ^s CTi s CX) W u #5 0#ffi i ID \ NP «* ^_^ -v s CJ> s cn_aln ^s^ ^Sw CW H, C. f» s N r" N r E L + CM -E +-> u m 4- F CL.$

30 CM E f > - ) f ' = ^ Q Q. 00 0) -l-> Q) i Q. E J + -E P E Q) U ( 4- g Ln Dl, E < - 1 r ^z T3 ^" i- 4- JZ -E CD U E +J r > a> 00 M- c ifl ja s- -M 3 r +-> M E 3 c C Q. r- </) ^^ L -l-> M (T3 r C E Q- i rc> B - > s- -a ) c u ' - r E (C l/l ( M- 1 > _, S- 3 #.. MM 4-> E S- 4-> +-> fc Q. 3 ^s CTi s CX) W u #5 0#ffi i ID \ NP «* ^_^ -v s CJ> s cn_aln ^s^ ^Sw CW H, C. f» s N r" N r E L + CM -E +-> u m 4- F CL. CL CM Ln c - i^ en t n ' CM S- > E 3 -E U1 ^ 00 N <X) i- E *i a. ( 00 1 > r X a r -M 3 «* n3 +-> +J r-- 4-> r u 00 r r ^ T ii r NJ B i r S- r +> l-* +-> a. r <*- E n -a en r E 00 r r^ E _E E r- -5 -Q i E S- r 3 z -(-> L/0 El

31 l -l-> 4- «=!- r < > d II s: JS V J 7 ^ CL c en II c +-> c c r- tn 1 +-> <NJ a. Q. #* E 00 u J S- ^ 3 CM 00 un c ) 03 M S- i CL II 00 >,_ *i JZ (13 -!-> 3 t +-> -l-> r C r T3 S- 0) CJ n3 M- S- I Q. > IS) l -i-> (T3 ra C un cr> r- 00 IA 1 r-. C S- r 4- <u a i c T3 f c ^ (0 (V a; i- 13

End view f rcket nzzle lking upstream. calesced shck structure Figure 16.

32 End view f rcket nzzle lking upstream. calesced shck structure Figure Crss-sectinal sketch f the calesced shck structure at the nzzle exit.

P tr n/m c (psia) Vane height, cm (in.) 0.32 6.87 x l 0 (978) 5.09 x 10 6 (738) A 3.44 x 10 6 (499) pen - h v = 0.521 (0.205) half-filled - h v = 0.394 (0.155) filled - h = 0.

33 P tr n/m c (psia) Vane height, cm (in.) x l 0 (978) 5.09 x 10 6 (738) A 3.44 x 10 6 (499) pen - h v = (0.205) half-filled - h v = (0.155) filled - h = (0.105) (a) ne Windward side Figure Static pressure distributin n the surface f the spin vane as a functin f chrdwise distance frm leading edge.

P tl, W (psia) 6.87 x 10 (978) 5.09 x 10 6 (738) A 3.44 x 10 6 (499) Vane height pen - h v = 0.521 (0.

34 P tl, W (psia) 6.87 x 10 (978) 5.09 x 10 6 (738) A 3.44 x 10 6 (499) Vane height pen - h v = (0.205) half filled - h v = (0.155) filled - h = (0.105) ne (b) Leeward side Figure Cncluded

NOTE ON A CASE-STUDY IN BOX-JENKINS SEASONAL FORECASTING OF TIME SERIES BY STEFFEN L. LAURITZEN TECHNICAL REPORT NO. 16 APRIL 1974

NOTE ON A CASE-STUDY IN BOX-JENKINS SEASONAL FORECASTING OF TIME SERIES BY STEFFEN L. LAURITZEN TECHNICAL REPORT NO. 16 APRIL 1974 NTE N A CASE-STUDY IN B-JENKINS SEASNAL FRECASTING F TIME SERIES BY STEFFEN L. LAURITZEN TECHNICAL REPRT N. 16 APRIL 1974 PREPARED UNDER CNTRACT N00014-67-A-0112-0030 (NR-042-034) FR THE FFICE F NAVAL