CIRCULATION LIST COPIES TO: Messrs J.C.Floyd R. H.Lindley J .Chamberlin F.Brame G.Hake R.Marshall M.D. 'IUller G. Oscar D. Rogers M.Pesando I.Liss J.Lucas s.Kwiatkawski A. Th001ann A.Buley S, Wh iteley J ,Hodge J ,Cohen w.B. tAcCarter T ,Roberts A.Crust for n.c. A.F. (12) Performance Group ( 3 ) Library D.Scard H.MacDougall COPY N01 l 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 2') 21 - 32 33 - 35 36 37 38 ARROW PERIODIC PERFO,tMA CE "IBPO.fil'...:...ll INTRODUCTION This is the elevsnth of a series of per1 odic performance r eports f or internal usage, t o be issued from the Technical Design Department. This report is divided lnto t hree major sections:- 1) Performance 2) Drag 3) Propulsion l Ail1.0IJ l PERFORMANCE WITH J 75 ENGINES C,G, AT 29.5% M. A.C. The following Arrow l performance estimate is bas8d on drag data of Periodic Performance Report No. 9, seemction 2, and revised J 75 installed engine data, see section). It should be noted that the perfor~ance , shown is for an aircraft fitted with a 45 11 divorgeht ejector, and 4° up-aileron deflection above 45,000 ft. The 45" divergent was selected, instead of the 39" cylindrical, since it .is intended to ~quip the aircraft with this ejector for the major part of the test programme, subsequent to the first tew flights. The 4° up-aileron deflection above 45,000 ft. has been shown since it is planned 1 to fix the ailerons in this position, for the high alt,itiude portion of the, test programme, in order to evaluate the effect and behaviour of this aileron deflection prior to the installation of the more complex system on the Arrow 2. Aircraft wei~hts used in this report are from Weights Report ffo. 7-0400-4/4, issue 10, suitably modified for the divergent ejector. This includes test equipment and ballast to limit the aft C.G. to Jlj ~.A.C., and 1s therefore applic P.ble to the early stages of the "Phase l" test programme. Since the Arrow 1 is a test vehicle, rather than operatiooal,the form of presentation has been altered from previous ·reports, in the interests of flight pr ogramming and correlation of results. !!!illIT.: - ARROW l PERFORM illCE - 11 EERFOi!{ANCE UNDER I,C,A,O,STAl~DARD ATMOSPHERIC CONDITIONS Take-off Weight with full Internal Fuel ••.•.•...•.•....•.• LB. Operational Weight Empty ••.•• , ... . , ..•.....••••••.•.•••••• LB. Half F'tlel Weight . • • • • • . • • • • . • . • • . . • . . . . . • • • . . . . . . . . . . . . . • • LB. Normal Design I.anding Gross Weight AIR 7-4: MIIr-5-57O1 ..• LB. Wing Loading at Take-off Weight with full Internal Fuel, .•..... ••• .................... LB/SQ.FT. Power Loading at Take-off Weight with full Internal Fuel ••...•••.•..••..•.....•.•• LB/LB.Thrust. True Airspeed in Leval Flight at Sea Level at Half Fuel Weight }Aaxiraum Thrust (A/B I,it) ••••• •• •• •••• •. •••••••••• •••••• .. KTS. Military Thrust (A/B Not Lit)•••••••••••••••••••••••••••• KTS. Max True Airspeed in Level Flight at 40 1000 1 at Half Fuel W~ight Maximum ThM°\st (A/B Lit) ••••....•....•....••...•..•.....• KTS. CEILING:- 50O F.P.M. Rate of Climb Ceiling at Halt Fuel Weight MaximUlll Thrust at 1.5 M.N~ (A/B Lit)••••••••••••••••••••• Fr. RATE OF CLIMB: - Steady Rate of Climb at Sea Level Half Fuel Weight Maximum Thrust at .92 M.N. (A/B Lit)••••••••••••••••••• F.P.M. Military at 527 KTS.(A(B Not Lit). 0•••••••••••••••••••• F.P.M. Steady Rate of climb at 50,000 rt. Half F~el Weight Maximum Thrust at 1.5 M.N. (A/B Lit •••••• .' •. ••••••••••• F.P.M. TIME TO HEIGHT:- Time to Reach 45,000 ft. and 1.5 M.N. from Engine Start at Take-off Weight with full Inter1>4l Fu~l Maximum Thrust (A/B Lit)••••••••••••••••••••••••••••••• MINS. MANOEUVRABIL1Tl:- Combat Load Factor at Half Fµel Weight Uaximum Thrust at M.N. = 1.5 at ~5,000 tt.(A/B Lit) '.£.Mk.OFF DISTANCES:- i: Take-off Distances over 50 ft. Obstacle at Sea ~evel at Take-off Weight with full Internal Fuel Maximum Thrust ( A/B Lit) ..•.•.•................•••..••. Military Thrust(A/B Not Lit)••••••••••••••••••••••••••• Maxim'Ulll Thrust Hot Day(A/B L:i.t) ...•..... , ... , •• ••• • •• .. PLACARD SPEED OF AIR 7•4 Fr. .FT. .FT. 68,765 48,922 58,892 53,892 56.l 1.82 700 645 50,JOO 37,600 10,530 800 6.0 4,700 11,800 7,500 LANDING DISTANCES:- Landing Distance over 50 ft. Obstacle at Sea Level at Normal Design Landing Gross Weight... . . . . . . . . . . . . . . . .. FT. 6,600 STALLING SPEED:- True Stalling Speed in Landing Configuration at Half Fuel Weight at Sea Level••••••••••••••••••••••• KTS. 119 I ,. :!.: . l- r--_.._ i '. 11 t, ; ; I ,.--- L , 1 ., l t-, · I .. :.L ! : . L, ! I ,. ! ' r . • ij r ' .- . , .. l r, ~,f:-'1~ - i - I IT • :~ j' I • • i' ....l. ~ • .l . ' • ' t·c• " 'Lt~, ., r:r: J-1+ T '~L: -~ ~ I l. .• :· ·r ·~ .j- er C :. i: ,,. IU ,<< '-: , ,,, TiH . 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Arrow periodic performance report no. 11

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