I♦ National Research Council Canada C. J.S.T.J. Aeronaut i ea] and Me chani cal Engineering Lib rary Conseil national de recherches Canada I.C . J.S. T. Bibl ioteque d ' aeronaut ique et de genie mecanique Reportno.: QC A-Jl • ·- •• j - .i . ; • I· . ·-t ~+.- - ., I I I --- + - L. ~~- ~~ I I -l .3k ~ L--~-1--, J j -.- I -1 .i. I I J ' .... ➔ -: I.. . fc... ... ~1- , : ii $ I r t~i- 1 ·1 .L .:., . ·~ May, 1956. B F- PERFORMANCE r, The following CF-105 - Orenda r.s. 13 performance estimate is based on the wind tunnel confip;uration designated B2V, W, &, 0 Ns Dg_4 (except that the nose angle has been reduced to 30°) The particular feature of this configuratior is the ext0nded, notched and cambered leading edge of the wing. The drag of tbis configuration has been summarized in prevkus monthly reports. The drag usfld is +,liat given in monthly report 6 with t.he C.G. at 29.5% M.A.C. in accordance with the planned fuel sequencing to give a C.G. position of 31% M.A.C, on firing the Sparrow II missiles. The increased weight of the Sparrow II pacK over that of the Falcon pacK is lareely responsible for the 1187 lb. increment in operational w<>ifht empty since the 4th monthly report (the last CF-105 Orenda PS 13 performance issue) The Orenda PS 13 engine data has been completely revised. See Section 3. The most significant change has been the slightly decreased thrust in altitude below 1. 5 M. N. and a considerable increase in thrust at the higher Mach numbers. The specific fuel consumptions are improved epproximately 10%. The pertinent CF-105 - Orenda PS 13 performance changes are listed helow1 6 Combat 'g' at 1.5 I.I.~. at 50,000 ft. 6 Maximum speed at 50,000 ft. 6 Combat ceiling at 1.5 M,N. 6 Combat mission fuel (200 NM radius) = -.11 = + 120 Kts. = - 1500 ft. = - 957 lb. LOADING AND PERFORMANCE - 8 Extract P/Perf/102 Vol II WEIGHT: Performance Under I 1C1 A1 01 Standard Atmospheric Conditions To R,C.A,F. Specification AIR 7-4 With Two PS 13 Engines Take-Off Weight with 14,553 Lb. Fuel (73.3% Max) •••••••••••••••••Lb. May, 1956. Operational Weight Empt7 ••••••·••••••••••·••••••••••••·•·••••••••Lb. Combat ffeight (1/2 Fuel) •••••••••••••••••••••••••••••••••••••••••Lb. Landing Weight (With Reserve Fuel+ Missiles) ••••••••••••••••••••Lb. Wing Loading at Normal Take-off Weight •••·•••••••••••••••••••••L~/Sq.Ft. Power Loading at Normal Take-off Weight •••••••·••••·••••••Lb/Lb. Thrust 56,119 41,566 48,843 43,356 44.7 1.25 SPEED True Air Speed in Level Flight At Sea Level at Combat Weight Maximum Thrust A/B Lit ••••••••••••••••·••••••••·••••••••••••••••Kts. Maximum Thrust A/B Not Lit ••••••••••••••••••••••••••••••••••••••Kts. True Air Speed in Level Flight at 50,000 Ft. at Com'tet Weight Maximum Thrust A/B Lit •••••••••••••••••••••••••••••••••••••••••Kts. CEILING Combat Ceiling at Combat Weight, Rate of Ci imb • 500 F.P.W. Ma ·cimum Thrust at 1.5 MN. A/B Lit ••.. ., .• ••• ........... ., ••••••• Ft. RATE OF CLIMB Steady Rate of Climb at Sea Level, Combat Weight Maximum Thrust at M.N. • .92 A/B Lit ••••••·••••••·••·••••••••'•P,Y. Maximum-Thrust at 530 Kts. A/B Not Lit ••••••··••••••••••••••••'•P.M. Steady Rate of Climb at 50,000 Ft., Combat Weight Maximum Thrust at M.N. • 1.5 A(B Lit ••••••••••••••••••••••••••F.P.M. TIME TO HEIGHT Time to 50,000 Ft. M.N. • 1.5 from Engine Start at Take-Off Weight * 720 670 1,260 62,500 61,500 23,800 12,400 Maximum Thrust A/B Lit •••••••••••••••••••••••••••••••••••••••••Mins. J.9 MAN OE!JVRABILITY Combat Load Factor at Combat Weight Maximum Thrust at M.N. • 1.50 at 50,000 Ft. A/B Lit 1.88 ~ Placard Speed• 720 Kts. Extract P/Perf/102 TAKE-OFF DISTANCE UM Take-Off Distance over 50 Ft. Obstacel at Sea Level at•·•·•·•• Take-Off Weight m 56,119 Lb Maximum Thrust A/B Lit ..........•............•..........• Ft. Maximum Thrust A/B Not Lit •••..•.•....•...•.............. Ft. Maxilllum Thrust Hot Day A/B Lit •••.••.•......•..••.......• Ft. LANDING DIST AllCE 2,420 J,640 3,000 Landing Distance ov~r 50 ft, Obstacle at Sea Level a t Combat Wei ght Ft, 5,060 STALLING SPEED True Stalling Speed in LanJ ing Configuration at Combat Weight at Sea Level .............................................•...• Kta. 105,5 RANGE Combat Radius of Action at 50,000 Ft., Climb at M.N. • ,92, Cruise out at M.N. • 1,5, Combat for 5 mins. at Y. N. • 1,50, Cruise Back at M.N. • ,92, 15 Mi n. Stack at 40 1000 Ft., 5 Min, Fuel Reserve on Landing High Speed Mission with 14,553 Lb. Fuel•••••••••••••••••• N.M. 200 High Speed Mission with Full Internal Fuel••••••••••••••• N. M. J81 Combat Radius of Action at 50,000 Ft. Mission as above except Cruise Out at M. N. • .92 Maximum Range Mission with 15,396 Lb. Fuel•••·•••••·••••• N. M. MaxilllUlll Range Mission with Full Internal Fuel•••••••••••• N,M, Ferry Range Mission at Economical Cruise Speed (M • ,92 and Height, inc l uding 15 Mins. Stacking at 40,000 Ft., 5 Min. Fuel Reserve on Landing Range with Full Internal Fuel and 500 Gal. - External Tank. N.M. JOO 510 1,738 !t111'1 !75t 1 _ -~ t 1C.F / 0...S 1 -- -~ P/PftF/1oe vi,1-izt _I f S.. l.J £ '4 G.) hi£~ -l---l--+--'----r-·+--+--,--.--.- .1:1.A-t.J,,6 j ' "'i,H )IF1'£/\.BURN..Sl<.5l l.tT . ·· j I ;_-, -~ - - I {----+l~~---l'--+-+-4--l--+'-'-f--",l---f---i--+:---+ \.. I t tU.lfr H 7 J_: -J-..L-+-'-..,..-f--1-t_.... I -+- I i ·- ~~ _J ! _ £1/lQ +-I -- f .is:~"'½---+--+--r'-+-~:+-:-+:-:'+:-"t-:-:--t-'-:-t-:::-:7r'--i-ct-;,f~,-f---:-'t"c:ct-,;-:t--.ir,tr.;~-rt- ..__;:,.,,1=-1.:.::.:..i...:..:+.++~--'1 rr·1 _ t FQ --1 -~· .5 ± I -r . ' - ,f ~ r -1 - r -~ . .j . t f - - . ---+--+--+-+-+~~-+--+- ,, T. -~---r- .. '-+--+--+ , -- -l ! r- _1_Ll_.c.L....Ll...:l!.- ' ftllALTV.¥ . I Jis, ~ I ' SS', , !f'?7WJ.SE10 , OS f;,I ";J,1,'?"7:::> r>..L :?>lll>'..f.S10 ~ 1- ; ~ -+- -~ "" I -~_.,,- SECRET ,ay, 2: CF•l'.J5 DRAG .H!l'E ,I◊ drnt: rC!vision 1as bee 1 made s1nce 'l10nthly report llo. 6 SECRET Extract P/Power/56 3: PROPULSION No revision h<1s l:.,een made t o t he JT4-A- 25 (J- '/ 5) engines, 'rhe Orenda P, S. 13 en~ine data has been completel y revised, The revision has Leen t aseJ on P,S, 13 eneine non-dimensional performance data (refer ence Bl2- 56 dated April, 1956) Instal l ation corrections applied to this are discussed briefly below, The tota l pre ssure r ec overy for the P.S, 13 was estimated on the basis of the Lewi s Lal:.,oratory tes t. a with t he J-'/5 confitsuration, (Ref: P/Power/6'.J) The on1y ge ometry eh 1nge nece :· sitated by the P,S, 13 engine was t he '/,1% increase i n int.ake throat irea faired within a lengt h of 49 11 into the i niti'll ...i iffuser, It is considered t o be within .:!: • 5%. The spil l age Jrag was est i mated on the basis of t he Lewis laboratory tests. Because it is dependent onl y on the geometry f or ward of the inlet l i p face and the external lip shape , it is Je~tical at t he same inlet mass flow ratio, The ejector performance is for a 4'.J" Jia;r, ter (1256sq. in) secondary shr ouJ with a 6'.J sq, in, b 'pass inl et area, Pu:,1pin~ characterist i cs are obtained from NACA RM E52L24, The thruat ( nozzle chockeJ ) is then calculated in t he usual manner fr om 'If-I less inlet momentum (!\') less spil • age drag g where:- Pa= runbi <.'! nt ~;:ft ·-t +- - '17 , • ,.. ' 1-t!'I .... • .... ' fr' j 1 + ':r:i ..... I ; :-tii- .. . rifl H t. ' t + F •+ i;ii

CF-105 monthly performance report no. 8

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