L,Ounc Canada C. l.S . T.l. Aeronautical and Mechanical Engineering library Report no. : oc ha s been □ [ZI I.C . I.S.T . Bibi ioteque d 1a€ ronautique et de genie mecanique 4vR.a C' f=°J D5 downgrad ed to : de-c las s ifi ed M-R -;; by (Na me) : S fvl.)). J./. e'{t r ~ e (De pt J D lt,1~ Cooed i oof-oc Acuiss ) Dat e: Lk,j L.//19:). • CF-105 MONTHLY PFfil'ORJ.!ANCE REPORT - 2 Introduction This is the second of a series of monthly performance reports internal usage, to be issued from the Aerodynamics Department. Only minor change has occured since the first report, and applies only to CF-105 Performance with Pratt and Whitney JT 4A-25 Engines. This alteration is due to a reduction in the ejector performance estimate for the JT 4A-25. The pertinent changes are noted in their appropriate sections. Successive reports will present the latest data, with the altera tions from the previous report noted. The report is divided into three major sectionsi- 1. CF-105 Performance 2. CF-105 Drag 3. Engine Data SECRET • AIRCRAFT: FILE No TITLE • ISSUE NO A . V ROE CANAD' LIMITED MALTON • ONTARIO TECHNICAL DEPARTMENT (Aircraft) CF-105 C1assification cancelledjchanged to ~~;??,,~::.':/~ ...... . CF-105 iWJ'TEL" PERFORMANCE REPOR.T ( Issued Mid-Mor.thly) This is Copy Number ••••••~••••• Issued to Date .. ijOV.l5.l955 ....... . PREPARED BY CHECKED BY SUPERVISED BY APPROVED BY REVISION No REVISED BY APPROVED BY DATE REMARKS REPORT No l.'onthly Re port No.2 SECRET No OF SHEETS·------ ----J N~C - Cl9TI AERO/ M.,E. LIBRARY 89:- 05 - l 1 BIBLIOTHEQUE A{no / G.M. C:NRC - IC:laT DATE DATE DATE DATE lA QF-105 PfflFORMANCE W!ffl PRATT AND WHITNEr (J-75) JT M-25 ENGINE§ Cc ,a, = 22% MAQ} SECREf The following CF-105 • (J-75) JT 4A•25 performance estimate it ased on the Wind Tunnel configuration designated B2 Vi lf1 E10 ~ D8.4. The particular feature of this configuration is the extended, notohed, and cambered leading edge of the dn_g. The drag of this configuration is summarized (extract P/Aero Data/58) and is presented in section 2 of the CF-105 Monthly Performance Report No. 1 issued October 1955. The considerations for the installed engine data is BUllllllarized (Extract P/Power/51) and is presented in section 3 of the CF•l05 Monthly Report No. 1. However an error has been made in the ejector calculations, and the reTision of the thrust with full afterburning 1e given in Section 3 of this report. Only this alteration has been allowed for as changes to fuel conl!IUIIIPtion, and non afterburning engine performance would not be significant. The pertinent CF-105 performance changes are listed below. ~ Combat tgt at 1.50 M.N. at 50000 feet = ~ MaxillUJI speed at 50,000 feet = 37 lets. ~ Combat ceiling at lo50 M.N. = - 1000 ft. SECRE • • • P/Perf/105 ( Appendix) WEIGHT: LOADING AllD PERFCRN '\NCE Performance Under 1: • . \.C, A. Standard Atmospheric Conditions To R.C.A.F. Specification AIR 7-4 ( '1/ith Two J-75 Engines) Take-Off Weight with 15,298 Lb. Fuel (77.1% ~a.x.) ••••••••••••••••• Lb. Operational ~eight Empty•••••••••••••••••••••••·••••·••••••••••••• Lb. Combat ~eight (1/2 Fuel) •••••••••••••••••••••••••••••••••••••••••• Lb. Landing "·eight (Ylith Reserve Fuel + l.lisaile s ) .............. ••. •• •• Lb. Wing Loading at Normal Take-Off Weight ·•·•·•••••••••••••••• ~b. /sq.Ft. Power Loading at Normal Take-Off Weight••••••••••••••• Lb. /Lb. Thrust SPEED True Air Speed in Level Flight At Sea Level at Combat ''/eight MaxiDnlm Tllnlst . • • • . • . . • • • • . • . • • . • . . • • • • . • . . . . • • • • • • . . . • . • . • . • . . • • K ts. Military Tllnls t .............................................. • . Cil • • K ts. True Air Speed in Level Flight At 50,000 Ft. at Combat Weight L'axi.mum Thrust Kts. CEILING Combat Ceiling at Combat Weight, Rate of Climb: 500 F.P,M. Maximum Thruet at 1.5 M.N. ·••••••••••··••••••••••••••··••••··•••••• Ft. RATE OF CLDIJ3 Steady Rate of Cli~b at Sea Level, Combat ~eight Maximum Thrust at W.N. = .92 ••••••••••••••••••••••••••••• F.P.M. Mil1tary Thrust at 530 Kta. •••••••••••••••••••••••••••••• F.P.M. Steady Rate of Climb at 50,000 Ft., Combat Weight Maximum Thrust at M.N. ~ 1.5 ••••••••••••••••••••••••••••• F.P.M. TillE TO HEIGHT Time to 50,000 Ft. M.N. = 1.5 from Engine Start at Take-off Weight .. 58,982 J.1ax1Dnlm Throat ••••••••••••••••••••••••••••••••••••••••••• MANOEUVRABILITY Combat Load Factor nt Combat Weight Maximum Thrust at M.N. ,. 1.50 at 50,000 Ft. Combat Load Factor at Combat Weight Maximum Thrust at M.N. = 1. 70 at 50,000 Ft, t Placard Speed n 720 Kts. Mina. 58,982 43,684 51,33.3 44,200 47.0 1.61 t 755 640 1,no 51,400 15,800 6,700 4.6 • ....... '2.;' TAKE-OFF DISTANCE Take-Off Distance over 50 Ft. Obstacle at Sea Level Take-Off Weight = 58,982 Lb. SECRET 1 • Maximum Thrust ....................•.............•... Military Thrust ........................................... ., .. Maximum Thrust, Hot Da:y ..•.••.•.••.•.•.••..••••••••.•.•••.••• ft. Ft. Ft. '3,400 6,7ob 4,600 LANDING DISTANCE Landing Distance over 50 Ft. Obst~cle at Sea Level ut Combat Weieht Ft. 5,300 STALLING SPEED RANGE True Stalling Speed in Landing Configuration at Combat ~eight at Sea I.,evel ••••oo•••o•• .. •••<»••i=t••••••••••••••••••••••••••••••••• Kt·s. 110 Combat Radius of Action at 50,000 Ft., Climb at M.N. = .92, Cruise out at !l.N. = 1.5, Combat for 5 Mins. at M.N. = 1.50, Cruise Back at M.N. = .92, 15 Min. Stack at 40,000 Ft., 5 l1'.in. Fuel Reserve on Landing High Speed Mission,with 15,298 Lb. Fuel .. ••••••·•••••oo• .. • N.M. 200 High Speed l,,ission with Full Internal Fuel ............. o ... N .M. 309 • Cor:.bat Radius of Action at 50,000 Ft., Y.ission as above except climb at 530 Kts. and cruise out at l.l.!I. = .92 Maximum Range Mission with 15,298 Lb. Fuel ............... 0. H.M. 406 Maximum Range Mission with Full Internal Fuel ....... o ...... l! .M. 605 Combat Radius of Ac_t~on at Sea Level, Cruise out at .6 M.N. and Combat at M.N. = .92 at Sea. Level, Crui:Je Back at .92 M.N. at 40 1 000 Ft., 15 Min. Stack, 5 !Unt Fuel Reserve on Landing Sea Level Mission with 15,298 Lb. of Fuel Sea Level Mission with Full Internal Fuel •••••••••••••••••o Ferry Range Mission at Fconomical Cruise Speed (M = .92 and Height, including 15 Mins. Stacking at 40,000 Ft., 5 Min. Fuel Reserve on Landing Range with Full Internal Fuel and 500 Gal. - Fxternal Tank N.~1• Range with full internal fuel ••••••••••••••••o••••••••••••• N.M. 325 1.70 1,859 1,609 ,£",e,e: //e F~ IDBt:TAci• E t-~, -+-,-9'1t-, ~-m*,~++--+----+---+-h+--+--~•__,I _ __;.---'.-, +,___·-=.,+. --=-+---t---,1-~-+_ -.. ,-+-.-=_i-=!_=-~~lc..c.· __ ,=i..:...,- . . . j - -- (j ' ___'.;-i.:.,;.., i-: . I , - - • - i . I· >-2:c..,.j ---1-+---l---h--l'=-+=-- +---i---<.....:....l--+---+I ..:...· . -+--+-- .j ~ ii-_-+/ r-----!, - r,..,-!-v----+-+--+_----1, 1-. -+--!-+---+--. 11-+:----+---+l--C.....-t...j___j_.__j.__J _ _j_~ _---1-L--l .-+- -t---+...:..:.....- S--, -?~ --+-~- ++-_- _:-_-·..,·+_-'-_-++- -+- +---+---+-+--l-~-· .... 1_·--l-·- l ( -I i t 1 . i-Z>-"-<,--'--:..... +----+-- r _ .. , -+----+--+--+--+---+- +---r , i-:- i-;;;~ • + 1 -+. - +---+--+-+--+--+-+--+-+---+---+---l--+--+---i-•--+·-f--+--+--·-+l·-----1--1~~1-"'-'.f'i....--'---h-- 1 LJ ' I I L-- - ' I· ~ ::li,n /2-,0 · i · . ! . :..--t.--- I I <1. I • ''-' I '--< .! . 1.--'-.__,' ' W r- 'I · _:_:.:.,. L.--- · !· j , ~ -..+-~ G Rou r ✓ o Rib N ---h--,--+----! ) • • . j 1--h--~ j I I -~;-. ~ -=--: -- L.- - r--- - --+---+----+-+--+--i--1---e-,.- -L-.....c - ,1--·~+-+---+---+----! _ I rhn/4r- 1..---L--· i ' j ' • ·T · I . ! -...,' U,'-... I I I-- -- - J--+---+-+----+----,.--1--+----1-+-·-++- l---+---+-~--l~-1---+- I 1' • , ~ i I .,., • \· e- - ·---+---+-'---' I _+----+---+-+--+---l--1---· +-' _t.-"-J...--+-+--+---'1----l- - ~ -+----+-'-+--1---~1----+-j---l ,,_ , ,,.._ U ~ ~ f--- ,=/,=,-c~F//O~ 0 ., ......... - ...... -- - ·; r ~ ; , . .,.; I ' l -I I c, · •· -'--~-·~~ . . 'I . I . ~ -= --L 1-~ ~1--;-:- _ • • I , · ~ t •-·+ci .-'--1-,--1--· ---:-·1L.-,-t-,-~-+--+- ,-.,...,.....-~ ......... .., 0 0 0 "" C, 0 a Lr, SECRET "The drag of this configuration is summarized (Extract P/Aero Datai.58) and is presented in section 2 of the CF-105 Monthly Performance Report No, - r k issued October 1955." No Revisions have been made. • • • 3. CP'-105 INSTALLED ENGINE DATA 1 (J-75} JT 4A-25 ENGINES SECRET The methods of estimating installed engine data and the subsequent installed engine data estimates (Extract P/Power/51), has been presented in section 3 of CF-105 Monthly Report No, 1. However an equation used was found to be in error and should readi - where Me (engine mass flow) replaces M (duct mass flow). This only produces a significant change with A/B lit and accordingly only this change has been made at this time. Figo 13, net thrust with afterburner lit, versus mach, no. and altitude, then has been revised and reissued in this report as fig. 13 issue 2o • • • on FAe.. I b ,.. -~- e:r'::fu: ~. ,, . J,AOOO 24,000 .:w,ooo 16000 I 1zpoo t 1qooo spoo 6,000 4-,000 } ' \ \ l I \ , 15,000' ... I 1 BYPASS ARBA 74 ,, EJECTOR DIA RATIO □ •. , SD'A( \ 13. r. JN.5 RAflO 0-58. NET THRUST CORRECTED FOR 5PIU .. AG£ DRAG i EJECTOR BOOST AND HEAT EXU{ANG ER LOSS . l ' \ I \ \. \ I I \ I 1-5 / \ )( ~5, 0001 , 550 1-S \ \ I \ I ' I • I \ t \ ✓ l,.5 ,0001 '- • fl(i 13 ( L5SUE2) \ \ SEC ET 1 1 I l i • •

CF-105 monthly performance report no. 2

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