.+...: =NACA AN INVESTIGATION AT HIGH SUBSONIC SPEEDS OF THE PRESSURE DISTRIBUTIONS ON A 450 SWEPTBACK VERTICAL TAIL IN


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1 cpy RM L54H23,, + : + =NACA  RESEARCH MEMORANDUVF AN NVESTGATON AT HGH SUBSONC SEEDS OF THE RESSURE DSTRBUTONS ON A 45 SWETBACK VERTCAL TAL N SDESL WTH AND WTHOUT A 45 SWETBACK Hrizntal TAL LOCATED ON THE FUSE LAGE CENTER LNE By Harleth G Wiley and William C Mseley, Jr Langley Aernautical Labratry Langley Field, Va ThlBmatm fal Wntdnsimkm ma c~m FOR AERONAUTCS WASHNGTON Nvember 2, 1954
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3 i? m  NACA RM L 54H23 NATONAL ADVSORY CC,XMTTEEFOR AXRONAU CS TECH LBRARYKAFB,NM lllllllll!l~~~~~~qllll i!l!  RESEARCH MEMORANDUM AN NVESTGATON AT HGH SUBSONC SEEDS OF THE RESSURE DSTRBUTONS ON A 45 SWETRACK VERTCAL TAL N SDESL WTH AND WTHOUT A 45 SWETBACK HORZONTAL TAL LOCATED ON FUSELAGE CENTER LtE By Harleth GWiley ~d William C Mseley, Jr s~ Y s An investigatin was made in the Langley highspeed 7 by 1ft tunnel at high subsnic speeds and several angles f attack f the chrdwise pressure distributin at six spanwise statins n a 45 sweptback, untapered vertical tail in sideslip The vertical tail was munted n a fuselage and tests were made with and withut a 45 sweptback untapered hrizntal tail munted n the fuselage center line The hrizntal and vertical tails had NACA 65AO1O airfils nrmal t the leading edge and had aspect ratis f 2 and 2, respectively Results indicated that the presence f the hrizntal tail slightly increased the value f sectin nrmalfrce cefficients n the vertical tail except at angles f sideslip abve abut 12 but did nt materially alter the nature f the lad distributin NTRODUCTON The Natinal Advi5ry Cmmittee fr Aernautics has underts&en a research prgram t determine the aerdynamic ladings n vertical tails as they are affected by varius design parameters and maneuver attitudes Calculated subsnic ladings and resulting stability derivatives f unswept and 45 sweptback tail surfaces in steady rll and sideslip at lw speeds are presented in reference 1 fr surfaces f vsrius aspect & ratis and hrizntaltail heights The effects f vertical lcatin f the hrizntal tail n the aerdynamic characteristics in sideslip f an unswept, untapered tail assembly were determined experimentally and
4 2 ~ NACA RM L54H23 theretically at lw speeds and at high subsnic speeds and presented in references 2 smd 3, respectively The present experimental investigatin was made in the Lsmgley highspeed 7 by 1ft tunnel t determine the aerdynamic ladings in sideslip at several angles f attack at high subsnic speeds n an untapered 45 sweptback vertical tail munted n a fuselage with and withut an untapered 45 sweptback hrizntal tail The hrizntal tail was munted n the fuselage center line at O percent vertical tail span The vertical and hrizntal tails had NACA 65AO1O airfils nrmal t the leading edges and had aspect ratis f 2 and 4, respectively Chrdwisepressure distributins were btained n the vertical tail at statins f 2, 3, 45, 7,85, and 931 percent vertical tail span Tests were made at, 4, and 12 angle f attack, thrugh an anglefsideslip range f t abut 23, and ver a Mach number range f 6 t 95 Reynlds number fr the testsj based n the mean aerdynamic chrd fthe vertical tail, varied with Mach number frm abut 19x 16 t 24 X 16 COEFFCENTS AND SY?fROLS The results presented in this bdy axes as shwn in figure 1 and are defined as fllws: paper are referred t the standard the cefficients and symbls used Cn Cm CN CB sectin nrmalfrce cefficient f vertical tail, Sectin nrmal frce qc sectin mment cefficient f vertical tail referred t 25c, Sectin mment qcz nrmalfrce cefficient f vertical tail, cnlbl cl + + c%b6rc6 ~ q ) rtbendingmanent cefficient f vertical tail abut intersectin f vertical tail and fuselage, x( cnlblttlcl + + c~b6 Z6c6 & ) pressure cefficient, 1  q
5 NACA RM L54H lcal static pressure, lbsq ft freestream static pressure, lbsq ft ~ freestream dynamic pressure, pvz T lbsq ft v M R a mass density f air, slugscu freestream velcity, ftsec tich number Reynlds number angle f attack, deg angle f sideslip, deg ft A~ * s incremental change f angle f sideslip due t verticaltail lad, deg expsed area f vertical tail, sq ft c E bv b lcal chrd f vertical tail, ft mean aerdzc chrd f vertical tail, ft span f vertical tail (measured frm center line f fuselage t tip f vertical tail), ft expsed span f vertical tail (measured frm intersectin f fuselage and vertical tail t tip f vertical tail), ft b expsed lcal span segment, ft z z distance frm centrid f intersectin f fuselage and vertical tail t expsed lcal span segment, ft vertical distance measured alng Zaxis, in Subscripts: 1,2, span statin indicated h hrizntal v vertical
6 4 NACA RM L54H23 MODEL AND AARATUS A drawing f the swepttail mdel used in the investigatin is presented in figure 2 tith a phtgraph f the mdel assembly shwn in figure 3 The untapered, 45 sweptback hrizntal and verticalsurfaces had NACA 65AO1O airfils nrmal t the leading edge and had aspect ratis f 4 and 2, respectively The tail surfaces were cnstructed f a steel cre verlaid with a glass fiber and transparent plastic finish t btain the airfil cntur ressure tubes were installed in the plastic surface cvering f the vertical tail alng cnstant percentage chrd lines at lcatins shwn in table Data were first btained at the utermst span statin (931bv), the tubes were then sealed and rifices were drilled at the next inbard statin (85b v),and s n Data were thus btained fr all spanwise statins at prgressively inbard lcatins n the vertical tail The tail surfaces were munted n a cylindrical bdy fabricated f sheet aluminum with an givalshaped nsepiece (figs 2 and 3) Tests were made with the mdels munted n the sting supprt f the Langley highspeed 7 by lft tunnel with the vertical tail munted in a hrizntal plane (fig 3) The chrdwise pressure distributins n the vertical tail were btained by directly phtgraphing the pressures as prjected by a cali brated, pneumaticptical system The system cmprised a series f pressureindicating units made up f a mirrr attached t a diaphragmt~e pressure cell One side f the pressure cell respnded t lcal rifice static pressure pz with the ther side referenced t freestream static pressure p such that the pressurecell diaphragm deflected in prprtin t the pressure differential pz  p & means f the mirrr, a pin pint f light was pr~ected n a calibrated camera screen such that the height f the prjected light was prprtinal t pz  p Each pressure rifice n the left and right surfaces f the airfil was cnnected t a separate indicatr unit tith the hrizntal spacing f the indicatr lights n the screen prprtinal tthe chrdwise spacing f the rifices n the airfil (table ) Direct phtgraphs were thus btained f simultaneus pressures which existed n bth surfaces f the vertical tail The sectin characteristics, nrmal frce and mment, were btained with an electrical pressure integratr which emplyed calibrated differential pressure cells t measure the difference in pressure between rifices lcatedat cmmn chrdwise psitins n each side f ;;M:H!WH!W
7 NACA RM L54H23 5 the vertical tail!heutput frm each pressure cell was weighted by resistrs t accunt fr that linear prtin f the airfil chrd ver which the subject pressure was cnsidered effective The ttal weighted utput f all cells was fed t a servperated, selfbalancing Wheatstne bridge circuit which directly indicated the summatin f all pressures ver the airfil chrd Sectin nrmal frce was thus btained fr each span statin in terms f the prduct f cn times q fr unit chrd and span Sectin mment was similarly btained as qcmj by taking int accunt the distance frm the mment reference (25c fr these tests) t the centrid f the effective areas f each rifice fr the determinatin f the prper mment weighting factrs (table ) A mre detailed descriptin f the principles invlved in the design f the integratr is presented in reference 4 TESTS AND CORRECTONS The tests were made in the Langley highspeed 7 by 1ft tunnel thrugh a Mach number range f 6 t O% Reynlds number fr the tests, based n the,mean aerdynamic chrd f the vertical tail, varied frm abut 19x 16 t 24 x 16 (fig 4) Tests were made ver an anglefsideslip range f t 23 at angles f attack f, 4, and 12 Blckge crrectins, cmputed by the methd f reference 5, were derived as sm incremental crrectin t Wch number 8 N crrectins were made t the data t accunt fr the aerelastic distrtin f the vertical tail under lad n rder t determine the general magnitude and nature distrtin n the vertical tail during tests, hwever, static tests were made using a span lading representative f the high lads btained at high sideslip angles n additin, the theretical deflectins f the tail were cmputed accrding t the methd f reference 6 (The span lading used fr the static tests and the theretical ccmrputatinssimulated the lading n the vertical tail in the presence f the hrizntal tail as btained frm windtunnel tests at sngle f attack, 16 angle f Sideslip, ~d a ~ch n~ber f 95 (fig 5(a))!hestatic ladings were arbitrarily cnsidered applied at 27 percent vertical tail chrd) The experhnental and theretical deflectins are presented in figure 5 in terms f the change f singlef sideslip due t ver the verticaltail span As shwn in figure 5(b), the maximum value f Ap btained frm static tests was abut Og and reasnable apprximatins f the change in angle f sideslip ver the tail due t lad can be calculated by the methds f reference 6
8 6 NACA RM L54H23 Deflectin f the stingsupprt system under lad was small and was neglected ACCURACY OF DATA!l%eaccuracy f the riginal data, sectin nrmalfrce cefficient Cn, sectin mment cefficient cm, and pressure cefficient, are direct functins f the mechanical accuracies f the pressureintegrating and pressurediagram machines The data sre belieyed accurate within the fllwing limits: c~, t5 Cm *1, *O 3 REDUCTON OF DATA ntegrated chrdwise ladings were btained by the pressureintegrating machine n the assumptin that a squarewave lading with parablic fairings at the leading and trailing edges clsely apprximated the actual chrdwise lading (ref 4) Electrical resistr weighting factrs used in the machine fr the chrdwise integratins are presented in table Since sectin nrmal frce and mment were btained directly frm the pressureintegratingmachine in terms f qcn and qcm fr unit chrd, the cefficients cn and cm were simply btained by dividing machine results by the dynamic pressure q n rder t btain nrmalfrce cefficient CN and rtbendingmcment cefficient CB, a mathematical integratin f the variatin f sectin nrmalfrce cefficient ver the expsed verticaltail span was perfrmed The assumptin was made that a squarewave lading ver the spin,reasnably apprximated the actual span lading The value Of Cn at each span statin was cnsidered effective ver that segment f the tail span which extended half way t the adjacent span statins r t the tail tip r rt as apprpriate Actual numerical values f the span segments b assigned fr each span statin are presentedin figure 6 A summatin f the prduct f cn and the apprpriate span segment b fr each f the span statins results in the nrmalfrce cefficient CN = ~(cnlb~ cl+ + cn6b6 c6)~
9 NACA RM L54H23 7 Similarly, rtbendingmment cefficient CB ws btafied by assigning a mment arm 2 which extended frm the mment reference (junctin f the vertical tail and the fuselage) t the centrid f the expsed span segmentfr each span statin (fig 6) Thus CB = ~(cnlbl llcl + + z6c6)& RESULTS AND DSCUSSON h rder t present the results f this investigatin in the mst usable frm, cmplete tables f all sectin cefficients btained and pressure diagrsms at representative span statins and test cnditins are presented fr the vertical tail with and withut the hrizntal tail See tables *O V n additin, the results are summsrized in terms f span lading, sectin mment cefficient, sad nrmalfrce and rtbendingmment cefficients with shrt discussins f these parameters as pertinent resented in figure 7 are the spanwise variatins f cn ver the vertical tail tith and withut the hrizntal tail fr varius angles f sideslip and Mach number at angles f attack f, 4, and 12 The vsriatin f sectin mment cefficient Cm & tith sectin nrmalfrce cefficient cn at six spsmwise statins fr the vertical tail at sngle f attack is presented in figure 8 The variatins f nrmalfrce cefficient CN, and rtbendingmment cefficient CB with ~ fr the vertical tail with and withut hrizntal tail at varius lkch numbers and angles f attack sre presented in figures 9 and 1, respectively FYesented in figures 11 t 28 sre typical chrdwise pressure distributins btained at six spanwise statins n the vertical tail with and withut the hrizntal tail at $ = 4, 8, and 12, at a = and 12, and at M = 6, 85, and O~ Examinatin f the spsawise variatins f Cn ver the vertical tail with and withut the hrizntal tail fr varius angles f sideslip and Mach number at angles f attack f, 4, and 12 (fig 7) reveals that presence f the hrizntal tail slightly increased the abslute values f Cn n the vertical tail at angles f sideslip less thsm X2 (an increase attributed t the endplate effect f the hrizntal tail as discussed in reference 3) resence f the hrizntal tail did nt materially alter the nature f the lading n the vertical tail at any sngle f attack r sideslip At angles f sideslip up t 8 and singlesf attack up t 4, the spsmwise lading ver the vertical tail with and withut the hrizn U tal tail was generally rectangular Abve p 8, at ~gles f attack f and k, and abve p = 4 at an angle f attack f 12, there was
10 8 NACA RM L54H23 a relative decrease in lading near the fuselage juncture, a decrease pssibly caused by flw separatin ver the fuselage at high singles The endplate effect f the hrizntal tail is again apparent in the slight increase f CN and CB fr the vertical tail with hrizntal tail at angles f sideslip less than ~ = 12, (figs 9 and 1, respectively) Langley Aernautical Labratry, Natinal Advisry Cmmittee fr Aernautics, Langley Field, Vs, August 6, 197+
11 N NACA RM L54H Queij, Manuel J, and Riley, Dnald R: Calculated Subsnic Spm ads and Resulting Stability Derivatives f Unswept and 45 Sweptback Tail Surfaces in Sideslip and in Steady Rll NACA TN 3245, Riley, Dnald R: Effect f and Vertical Lcatin n the Aerdynamic Characteristics f an Uhswept Tail Assembly in Sideslip NACA Rep 1171, 1954 (Supersedes NACA ~ 2g7) 3 Wiley, Harleth G, and Riley, Dnald R: h Experimental ad Theretical nvestigatin at High Subsnic Speeds f the Effects f HrizntalTail Height n the Aerdynamic Characteristics in Sideslip f an Unswept, Untapered Tail Assembly NACA RM L53J19, HeM?er, Arleigh : Electrical ressure lhtegratr NACA TN 267, Herrit, Jhn G: Blckage Crrectins fr ThreeDtiensinalFlw ClsedThrat Wind Tunnels, With Cnsideratin f the Effect f w Cmpressibility NACARep 995, lg5 (Supersedes NACARMA7B28 ) 6 Zender, Gerge W, and E?rks,William A, Jr: An Apprximate Methd f Calculating the Defrmatins f Wings Having Swept, M r W, A, and SweptTip lsn Frms NACA TTJ2978, 1953
12 1 NACA RM L54H23 TABLE CHORDWSE RESSURETUBE QCATONS AND CHORDWSENTEGRATORWEXXTNGFACTORS FOR VERTCAL TAL 31 Tube Chrdwise lcatin, percent Chrdwise inte~atr veightings fr Cn cm 1 and $%1 2 and 17 ; and U25 handlg 1 ~ and K)9 6 and and and 23 % 75 $52 9 and and ~d 26 z: E ~d and 28 i; 1 J 14 * and 3 E s
13 NACA RM L54E23 11 TABLE SEUUON CHARACHR18TCS, SMTONO931b7 (a) a = OO M B, deg *6O 6 e6 6 a6 6 6 *6O 6 s Withuthrizntal tell n ~ S e226s , a % 611 * alz e4 C21 28 *33 46 Withhrizntal tail Cn % G1571 , b b b *8O 8 8O e8 ~ a a836  t2613 , a a2 ~29 b4 e e e452  e4782 sl 1 eo8 b * s ;:  aa2  #795  S b tll e3 b ~ b179  #934  e c * b9 18 s , , , a b398 s ~ e b13 e2 b921 G25 s16 12 cla ;: BO47  OE b278  b *2 a9 s25 *35 a3 b a a S15 17 t,
14 12 TABE  Cntinued SECCCN CEMRKTKR1911C!S,SJ?ATCMO931bv (b) a = 4 M ~6 6 e ~6,6 c6 $, deg Withuthrizntal tail Cn b e e e B498 cm a12 ez e With hrizntal tail Cn m *74  s e cm b715 a5 * a37 *42 8 s8 8O 8 ~8 8O eo % # b c a3 * c18 26 ~38 * e498  ~ # eo b34 ~29, a39 8 ~85 85 e85 *85 *85 85 e ; % eo18 b C31 e29 b O142  a a * e3 3 3 b e : 16 2 $564  b ~ c *3 b9 *21 s18 b43 a28 a25 * b * b2 e ,25,27 b95 95 S95 a95 95 e95 95 * : , ~ b14 # b34 *4 ~ eo * c3891 SO15 *2 sl , e17 25 ~25
15 NACA U4L~kH25 13 TABLE  Cncluded SEC!?JC%? CHARACTERSTCS,SJ?ATCNgmv (c) m = 12 M, deg e62 a6 a *6O 6 e Withut hrizntal tail c~ e561 , O?67  * cm sl b b3 O8 O5 Withhrizntal tail C* * b e22  e b435 cm b4 b ea e8 2 e , ~24  e538  a185  * e bl *O e , ao6 16 b5 33 n , :; a a 9 *O1 *OO b e b45 11 *2 6 eo18 b2 617 bsl 941 a b9 : 9O a 9O 12 9O fi ,299  a O1 e b3 b5 O , n b2 bo *952 *95 b b b c b351  a b *O a b15 n2 en b22 e ra~iia : L
16 14 NACA RM L54H23 TABLE 8FCCONCHARAC ERM CS, 8MCON 851+ (a) a = OO M B, deg 62 6O e6 2 *6O 4 ~ G Withuthrizntal tall % a858  # s b % O1O eo6 2 * 4 b34 b With hrizntal tail Cn * a S e5373 % DO7 1 a e42 b O e ~8, e88  * e c4172 , b *14 9 e b58 b *995  *1869 , S s bl b9 b e46 m ~85 *85 2 b B85 8 s * s85 23 *878  eo64  c136  ; b7 b2 ao *O21 25 e b b29 #21 b *64,92 b9 9 9O : 9 6 b9 8 b s a5269 *O1O 2 *O1O * *27 e25 S41 1O29 a Q tll 2 *O1O e ~ *95 2 a a41  e e b 61 e27 e eo b33 a49 b19 b
17 15 TABFi  Cntlnysd SECl?ONCHARACTERSTCS, 81A!?CRJ 85~ (b) CL=4 M, deg a6 2 a , c6 16 6O 2 *6O 23 Withut hrizntal tafl % s6sl ~6  b c542 % eo8 2 eo6 b15 s12 26 *71 ~65 59 e62 Withhrizntal tail % ~ C # c5463 cm a7 e,8 to ~ t 882,*8O a8 2 *8O 4 a 6 *8O H e * = S eo819 ~ m59 e CO1O5  # e * e565  * b9 b a i c * s a * # cl *3 ~28 ~ O36  #232  c * c a6525 sl 61 bll e24 m e48 ~63, O 2 *9O a9 4 6 a ;: b14  a897  s e # * *28 4 * a898  co1o $ b Cil bl 12 * # *95 6 b a744 *  t a all b bll c26 a41 a2 ~46 36 a822  eo s *337  s a b e
18 16 NACARM L54H25 TABLE  Cncluded SECTON CHARACl?ER19J?CS,EMTON 85bv (c) a= 12 M, deg 62 e6 6O e6 6 6 a 6 12 a6 15 Withut hrizntal tail ao e ,629  s615 cm eo6 6 b5 en * a95 With hrizntal tail Cn 889, * a5972 Cm, b14 * : 8 8 8O 12 b O * bal a a e *5416 O8 8 e7 ao16 b13 13 b73 6, e a5475 ao Cil a e a b a27 e4 sob8 61 9O b b9 12,9 15 a b b *O & b e a eo a63,952 b b O87 O a bl 1 eo8 18 s O1O s a *9 bll *2 66,  
19 N NACA RM L54H23 ~ 17 TABLE V SECTON CHARACT~nCS, EATON O7C?W (a) a = OO M B, deg b s6 e6 % 6 23 Withut hrizntal tail % ~ ~ *7223 , % * ao8 * b With hrizntal tail Cn c2z a7126s92  * a7552 cm b3 b b4 *O1O a e ,8 8 8 #8 8O aa S c a * *4 bll b13 c18 a94 77 # e # a e613 eo ~852 *85 e , s85 12 s c c a c s a73 * *245  e e27, b O b9 2 9O B O , e e72 #3 1 ao6 s17 b ~ a e sb b21 eo8 a19 *34 a36 67 e a e b95 % *67  l e *1OO * e *O1O a21 e25 s18 64 e83
20 18 NACA RM L54H23 TABLEV  Centinued SEOl?ONCHARAC ERSTCS, 81?ATON7bv (b) a = 4 M 9, deg a62 e a6 23 Withuthrizntal tail % 1OO5 ao a2822 , e a a7893 ml 4 e3 eo8 a2 e25 Clll s el16 Withhrizntal tail Cn a C ~7895 % *4 a9 b3 al c O 4 8O O 16 b e487  * ? a4 1 b4 $9 e8 b37 S11O #946  # a * *3 62 b S85 *85 2 S ~ , a68  a924  a a i = ti7869 b4  a5 bo8 17 c16 1OO 92 l C154  b15  b132  s e738  * c e2 b *1763 b O a *9O 6 B9 8 a9 e ao e b s18 b19 98 e96,9 al * # e *7172 # ~ : e #7595 *4 a e5 s15 b27 s C s e a * s e7839 b31 b7 a1368 ao8 1 *16 ,
21 NACA RM L54H23 19 TABLE V  Cncluded SECTON CHARAC3XR~CS, S?AYCN7 (c) G = 12 M, deg 62 6, ~ ;; Withut hrizntal tail % e u e a795 #3 bl bl With hrizntal ta%l b s a cm b2 *13 b7 bl ao16 b O  2 e8 8 2 *8O O 8 e8 12 e8 15 e , e1764 , b e bl e25 e 12,67 el16 bll O23  b a e eo g , e e85 15 l14 e143  e *385 b2 bll b66 98 allll ao e272  e , b 3 a9 bo18 a15 8 Sll b b9 9 : *9O 8 9O b c e3 1 a2 b5 ao8 O eo a *7783 b7 n 66 eo e69 b b b ,, , e bl19 ao6  a236 *O1O  a e6  b *
22 2 c!~ NACA FM L54H23 TASJ? v SEC!ONCHARACTERSj?CS, EO?ATONO45% (a) a = OO ~ O e6 ~6 6 e6 6, deg Withuthrizntal tail % *12  a C lc O23 la2596 h 3 b2 s1 e44 az 29 S131 a With hrizntal tail % 1O96  O lao % 5 b3 Cl # *1183 a  11s1  s lo819 ls28 1O465 * b m O67  b88  # e ~ b3 1 b27 e 96 b a15 ~85 85 *85 85 B e85, H 23 e al O le l eo862 ~58 b eo6 1O84  b b959 , a e9 9 9 *9O b9 b9 9 9 b co1o6  S ,64 1O273 b BO e , s a *95 a # S b b cl *12 eo6 s *443  ~ lo321 b3 b c12696
23 NACA BM L54H23 TABLEV  Cntinued 8E4X!ONCHARACERS?CS, S9YL 1ON 45t+ (b) u = 4 h! 6O 66 *6O 6 6 a6 6,6 6O e6 B, deg Withuthrizntal tail % c # la268 ls3218 % b364 a bll 86 b168 2 With hrizntal tail % c * a85711~ % 3 2 b b2 5 ao # *8O 8 a8 e8 8O : # s O 1*1483 z l e a3 *7 e3 O16 # *7 ~165  O48  s1265 , le625 ls898 b3 e24 a a b O s * O fi2 Sl b 63 *8 a 819 S135 b7 * s lal13 e2 92 e s4 ~ e149 eo *9O 9 9 b O s ls1349 le *5 s1,*37 b a412  s e b , b95 e a239 , Sil s bl W e4 * e2 e *3
24 22 NACA RM L~kH2j5!MBm v  Cncluded SEC?ONCFMRACKCERS!CS, STATON 45~ (c) a,=12 M, aeg, a e6 15 Withut hrizntal tall Cn 175 bl eb cl bl 1 bl al 22 With hrizntal tail a a cm *1 b397 eo e b b a * 61 bl O a b a533  e eo6 eo6 a2 37 a e : 85 8 a c ; a cl al eo6 bll 94 e O a b2 b2 b a5 92,9 b9 4 D Clll e = cl b 1 bl 49 *O1O b * e4897? al O6 sl a14 *2 e a95 a S a bl b a , e e b co6 *3 S15 26,38 53
25 TABLEV SEC!TCNCHARACTER181?CS, 8TATON3 (a) m = OO M 6 e6 6 6O c6 6, deg Withuthrizntal tdl cn ~ cm b a a 1 b2 12 e17 S Hlth hrizntal tail cn,q e s84161g cm * bl b b *d2 e e e8 8 ~8 8 *8O 8 *8O, , b s * b aooo l ,6 98 b? ao ~ m297  b m *8584 la *1 82 *2 e * e , a85 c z ;: b149  b , bl a7 S115 eo8 ~128 , a e e s 9381~1132 al 1 * , *149 a7 *7 e b9 9O 9O c b * *3 b s s1633 ,384  * ~ sw+ al e e e146 m S95 * a S133  B e * ~8673 le742 a5 b a ~978  a * s1312 a4 94 a
26 24 NACA RM L5JH23 TAME V  Centinued SECTONCHARAClXR191?CS, SATON3Wtv (b) u = 4 M, deg e a6 6 e Withuthrizntal tail % b93  O119  s a a a7327 lt s5236 W bl 1 &l  b3 *14 bll,87 *15 With hrizntal tell s214  s b s b l# cm cl cl * 2 bz *6 *3 a22 8O  2 8O 8 2 ba a8 16,8 2 *8O 23 a92  to * # S tl bl b bl 1 #4 a4 e eo8 e82s * e527  a829 lc1631a2896 ez cl b ~ b , : e85 e85 :; e c129  a *7627 le684 lt al l b b ,67 #5 DO b e432  b ~ , e4 ll s24 46 ~96 eo O a O 6 b O a a m a C144  a e81821s113 ls e5 b9 16,~8 666 e82 eo b c95 16 e985  eo87  $ * e t825 lo42o b4 ~23 *49 e8 ~826  ti27  b s31 b *5 911 ~16 29 e48 e am====+,& w 
27 NACA R14L54H23 TABLEV  Cncluded 8ECZON CHARACJ?ERSTCS,81?ATCNXC%V (c) a = U M $, deg e62 6 e6 2 6O Withut hrizntal tail Cn ~938 , ~ % 62 b 1 62 O With hrizntal tall Cn al a139  b b a9519 m a 8 z, e O 8O 2 8O *8O 12 8O e2b e e e35 S53 1O82  O168  m e b a a5 4 e ~ e3a  s b 3 eo6 e14 26 * allz e *11 cl bl O 2 b O O 15 l e a 94 8 la b35 b b b a e47 7 b a b95 2,95 4 b ?  e ~ e e b5 b7 5 a b134  e a *
28 26 NACA RM L%H23 TA3LE V SECTONCHARACTERSTCS, STATON2~ (a) a=oo M 6 c6 6 6O a6 6, 6 e6 6 6O $, deg Withuthrizntal tail c~ S k752 la513 la bll 13 eo Withhrizntal tail Cn a771  b22  S # b ~918 cm $5, #4 b a19 * ~ ~8 e e8 98 *8O : *94  s184  b b269  e s a7764 ls526 la2295 1s a b * ~ a #845 la1419 ls a a2 e28 34 m5 19 eo : e269  e b415  * ~ eo b a7 eo8 # a ~8776 lt1281 ls ? eo6 * e48 * ao8 *8 * b9 *9O 9 b9 9, * * O18,29 39,64,96 b? # e s767 la b44 e56 a?l l *125 a7 * *95 *95 95 a : b * b 12 b26 b39 a34 e63 e78 b823  S c e a *3 e14 b3 42 *57 *71 al4 121
29 NACA RM L54H23 27 TABLE V  Centinued SECZCONCEARACTERSTC8,STATCW 2bv (b) a = 4 M e6 6 a6 6 e6 #6 6O 6 6 6!3, deg Witbut hrizntal tail  a191  # a m o l&4222 cm 83 a b2 b a45 a14 With hrizntal tail % c t ~ a525  a79341s721, % b5 2 tll * *8O 8 2 ~8 *8O : 98 8 e la237 1, a b e38 a s8 a e le2577 h4 S17 26 ~36 e7 ~ eo a a a77751c1751, a a eo8 a81  e # a * O 1*2567 b e b a z O 6 b s ~ *7979 la e6 8 O eo * e a s9789 ls e n71 19 l1897 * * e e7943 ls b43 83 # #542  s a e 38 e
30 28 NACA BM L74H25 TABLE KU  Cncluded SECTON CEARACTERSJ!CS, STATON 2bV (c) a= 12 M, deg e62 6, O 6?: Withuthrizntal tail cn # B8118 cm e9 b 1 18 e b47 With hrizntal tail C* ,214  b774  b s fi692 ,8957 cm 18 *2 ~16 b3 36 e e82 8 e ;: a e b616s ,8325 * c32 b4 b74 98 e e28 b e : e448  O127  $665  # a e14 28 b e e *2 636 *73 b94 Qll ~6 92 a9 9O *9O O 12 9O b a to16 cl,16 32 b e239  C ~ b35 e67 e85 *698 b a eo e c b e *1818 ,2673 bzl *2 e28 e55 e65 e8
31 t t Figure 1 System i axea used sitive frces, mments, sngles, and velcities are indicated by arrws
32 3 NACA 22 \\\\\\\\\\\\ \ ~ secfi?4#1 S7 Cre Mu# SAE 43 Steel u Sictit? b+  (inches) Q ) * b (3M97L) Figure 2 hysical characteristics f mdel (Dimensins in feet unless therwise nted)
33 NACA RM L54H23 31 \  = > :,   (a) Fuselage and vertical tail L Figure 3 htgraph f mdel munted n sting supprt in Langley hi~ w speed 7 by 1ft tunnel ~
34 32 NACA RM L54H23 L838 (b) Fuselage and vertical tail plus hrizntal tail Figure 3 Cncluded,
35 * t 26x R 2 8 {6, L M figure k  Variatin f test Reynlds nuuiber with Mach nuder (Reymlds nuniber is based n the mean aerdynamic chrd f the vertical tail )
36 34 NACA RM L54H23 YLLOL: 1 1 r (a) Simulated a= lading n vertical tail, = 16, M = g~, in presence f hrizntal tail at and q = 746 lbsq ft T%ery ret Verticul til spun, in (b) Spanwise change in angle f sideslip f vertical tail Ap due t simulated experimental lading cnditin Figure 5 Spanwise change f angle f f vertical tail in presence f hrizntal tail fr shulated expertintal lading cnditin
37 , L_ L $s Q L _ Designates  Designates rifice sttim lcal span increnwfs Figure 612etailsf effective span Tr spanwise integratins Begnenta b and nmment t btain ~ and CB
38 36 NACA RM L54H23 Cfl p= M p Fugged symbk are fr 94 fuseage ph verticul fail Cf) c~ B=8 B=2 O(Z ~v) pefcenf (a) a = OO Figure T Variatin f sectin nrmalfrce cefficient with spanwise lcatin fr varius angles f sideslip and Mach nunibers  withut flags are fr fuselage plus vertical and hrizntal tails)
39 NACA RM L54H =2 Flagged symbk B= 4, me fr fusehge plus verfica~ fil 8=6 B=2 ~v, percent jjv= percent (b) a = 4 Figure 7 Cntinued
40 38 * FiACA FM L54H23, #9= M p=2,6 Cn C Fegged symbls u= fr 34 :[ $% [ F[ # fusehge phvertical fail p= 5 c~ u 5 [ 5 1, # ~b,percent v 2466L ~h, percent (c) CL= 12 Figure 7 Cncluded
41 NACA R&lL54H23 39 cm b A n flagged symbk are fr fus cm cm, # Cn c~ Figure 8 Variatin f sectin mment cefficient with sectin nrmalfrce cefficient at a = OO (Symiblswithut flags me fr fuselage plus vertical and hrizntal tails)
42 4 2 2 C* n , deg (a) a = OO Figure 9 Variatin f nrmalfrce cefficient with angle f sideslip fr varius Mach nunibersand angies f attack (Symbls withut flags are fr fuselage plus vertical and hrizntal tails) c~
43 3N, WCA RM L514H L 4 u A ~e9 (b) a)= 4 Figure 9 Cntinued
44 42 NACA RM L54H ! L ( 4 8 2,deg (c) Figure 9 Cncluded,~
45 NACA RM L54H23 43 c~? p, deg (a) a = N Figure 1 Variatin f rtbendingmment cefficient with angle f sideslip fr varius Mach nunibersand angles f attack (Symbls withut flags are fr fuselage plus vertical and hrizntal tails)
46 44, c* d , a eg (b) m = h Figure 1 Cntinued,,:::+ ~
47 NACA RM L54H23 45 c~ H,~e9 (c) a = 12 Figure 1 Cncluded
48 46 NACA RM L54H23 With hrizntal tail Left surfuce A Right surfce 3  &= 83 { p  p=,2 ~RRm?_ 5 Xic, percent ~+, percent (a) u = Figure 11 ressure distributin n vertical tail M= 6 Statin Og31bv;
49 NACA R&lL54H ~ ~ With hrizntal til withut hrizntal ti 1 1 A Left Right surface surfce ?=8, t 13 p m =, percent (b) a = 12 Figure 11 Cncluded
50 NACA RM L54H With hrizntal tail  =4 ~ withut hrizn hl t ii Left surfuce A Righf surfuce 3 ~= 8 $fc, percent 5 (a) CL = C, p ercenf f Figure 12  Rreswre distributin n vertical tail Statin M= 6 cm=mm!am
51 7N NACA RM L54H withut hr iznfal tt7i,lef t surfce A 1?~ght surfce t 5 5 f XC, percent XC $ percent (b) a Figure 12  Cncluded
52 NACA FM L54H23, 3 With hrizntal tail withut hrizntff tail p  L ef ~ surfuce A Right surfuce 35 Xjc, percent  % > percent (a) a = Figure 13  ressure distributin n vertical tail Statin O TOObv; M= 6
53 NACA R&fL54H , Surfuce surfuce 3 ~ (b) a = 12 Figure 13  Cncluded
54 52 ACAW L54H23 w ithuf hrizntal tuil =4m A Left Right surfuce surface p  5 XC, percent 5 xp J ercent (a) CL=OO Figure 14  ressure distributin n vertical tail Statin 47bv; M = 6,
55 NACA RM L54H23 53, Wifh 3 r hrizntal wif huf  +4 Left surface A Right surfffce 33 p c, percent *c> ercent (b) a = 12 Figure 14 Cncluded
56 54 NACA RM L54H23 Left surfffce A Right surfuce 3  # =83 p xc ) ement xc1 ercent (a) a = OO Figure 15  ressure distributin n vertical tail Statin 5bv; M = 6
57 NACA RM L54H23 withut hriz nful fil ::= ~ A Leff Right surfoce surfuce 1 1, ~AA XJ,percenf ~C, percefff (b) a = l Figure 15  Cncluded
58 y5 ccnw3m!3w& NACA RM L54H23 With hrizntal til 3 ) 1 wmuf hrizntal ti 1 Left Surft7ce A ~ight SUrfOC8, ~= g 5 5 Xc, percent Vc,percent (a) u = OO Figure 16 ressure distributin n vertical tail M= 6 Statin 2bv;
59 8N NACA RM L54H23 With hrizntal til 3 ~ Left surface A Right surfoce 3 p  = ~ 4 ~&dla ~ A A t 5 5 xc, percent ~c, percent (b) a = 12 Figure 16  Cncluded
60 58 VACARM L54H23 With hrizntoltoil 1  Left surfuce A Right surfffce *c# percent  (a) a!= Figure 17  Eressure distributin n vertical tail M= 85 Statin O%lbv j
61 NACA lm L54H23 59 With hrizntal tail with uf hrlzntl til  Left sur fce A f?ight surfce (2 5 ~C, percent 9C # percent 5 (b) a = 12 Figure 17  Cncluded 1
62 6 NACA RM L54H23 With hrizntltil withuf hrizntal til  O L e ft surfuce A Right surfffce   COama AA A%& p 2, 4 (? 5 5 m xc, percent ~, percent (a) a = OO Figure 18 ressure distributin n vertical tail M = 85 : ? Statin 8sObv;
63 NACA RM L54H23 ~ 61 1 s urfuce surfuce  z  ~~ ::& =2, AA 1 5 *~3 ercent (b) a = 12 Figure 18 Cncluded
64 62 NACA RM L 34H23 With hrizntltil withut hrizntal fil  A Left Right S UrfC8 s urfuce  9=8 (a) a = OO Figure 19  ~essure distributin n vertical tail Statin OyOObv; M= 87
65 NACA RM L54H23 63 withut hrizn tfai  = 4 O Left surfoce A Right surface   4~h, w~~ ;:%, 2, ~=, percent X4, percent (b) CL Figure 19  cncl~ded
66 64  cunl?mmeal NAC!ARM L341E!3  Left surfce A u ~g~ t surfoce b~~ ~ ~ () t n u & = u A A c) xc, ercenf $ff efcent (a) CL= OO  Figure 2 ressure distributin n vertical tail Statin 45bv; M= 85,r
67 N NACA RM L54H23 65 With hrizn fdfail,,  G  =4 ( Left surfce A Righf surfce,  1 1,, p 2 1 L Xlc,percent xc, percent (b) a = 12 Figure 2 Cncluded
68 66 NACA RM L54H23 Wifh h fizntol til withut hrizn t til w~ =4 A ~ ef t SurfOce Tight surfce z  5 $fc, percent 5 Xjc, percent (a) a = OO Figure Z1 ressure distributin n vertical tail M= 85 Statin 3bv;
69 WWA ll!l5j+eq3 withut hrizn t(7i? Uil  B 4 1 s Urfuce  ( d  p,** u 85 c, j!j c ~ercent 5 (b) a = 12 Figure 21 Cncluded
70 68 NACARM L34H23 with hrizn fuliui withut hriznfu fil  ~ S Urfuce Surfuce 1 (  5 (w xc} ercent (a) CL= OO Figure 22 ressure distributin n vertical tail Statin 2bw;  M= 85 
71 NACA RM L54H23 69 wi thuf hrizntal #a ii  : [ Left surfuce A Rjghf surface ,  5 percent 5 m X$c, percent (b) a = 12 Figure 22 Cncluded
72 NACA RM L54H23 With hriznful til withut hrizntal tail  Q L eff surface A Right s urfce  j9=8, ~J yc 5, percent F 5 Yc percent (a) a = OO Figure 23 ressure distributin n vertical tail M= 95 Statin g51bv;
73 NACA R&lL54H23 71 With hrizntal tail w i f but hrizntal tail 1  Left surfuce A Right surfffce   f~ 5 ~c, percent (b) cc= 12 Figure 23 CO~Ckded
74 72 NACA RM L54H23 With hrizntal til withut hrizntal tuil  L e f t surfuce A Right sur fce  f (a) CL= OO Figure 24 Fressure distributin n vertical tail &atin 85bv; M = %
75 ON NACA RM L54H23 u 73 With hrizntal til wif huf hriznful fuil  u  4 A Leff Righf W rfce Surface xc, percent 5 1 ~c,percent (b) u = 12 Figure 24 Cncluded
76 74 NACA RM L54H23 With hrizntal tail withut hriznfa tail 1 2 ~ f Left Right surface surfce  w,,~ ~ 5 5 +C, efcent %, ercent (a) CL = OO Figure 25 ressure distributin n vertical tail M= 95 Statin OTOObv;
77 NACA FM L54E23 75 Wifh hrizntal til withut h f)znfl fil  4 Surfuce s urfce  u )  f) n u, AA% ~L 1 7 xc? ercent (b) CL= X2 Figure 2 j  Cncluded 1
78 76 NACA RM L54H23 Wit h hri2ntl til withut hrizn tl fail  ( ~~ ( Left surfce A Right s ur face (  ( 4  Q u 5 xc# ercenf, (a) al = Figure 26  ressure distributin n vertical tail M= 95 Statin Ok~Obvj
79 NACA RM L34H23 77 with hrizntal fil withut hriz?ta tail  %m 1 Left A Right surfce s urfce (b) CL= 12 Figure 26  Cncluded
80 NACA RM L54H23 With hrizntal til withut hriznf al tt7il  r t Left A t surfhce s ur fce  49=8 w  b%) w *A fg 9= 2 ) A AA AK? 5 cs percent 5 Xic,percent (a) a = OO Figure 27  ressure distributin n vertical tail M= 95 Statin 3bv;
81 NACAml L5ME3 79 w if huf hrizntal til  G 1 A Left Right surface s uf fuce, 2  (?3 OmO ( ) AA AA2!2 4 5 %, percent 5 J%, percent (b) a = 12 Figure 27  Cncluded
82 8 NACA FM L54H23 With hrizntal til withut hcwzntal tail  A Left Right Suffuce S U~fUC x, percent w e) 5 +=, percent (a) CL= OO Figure 28 ressure distributin n vertical tail M= 95 Statin 2bv; >: GmEmmwTilF
83 MCA RML54H23 With hrizntal fail wifhu f hrizntal fail  t 7 surface A Right Surfffce f 2 5 %,percenf  y=,** # * (b) a = 12 Figure 28 Cncluded iacalangley