PERIODIC PERFORMANCE REPORT 14 PERFORMANCE OF THE ARROW 2 SE~~✓ AUGUST 1958 • • AIRCRAFT: ARROW 2 FILE MO, 72/PERF/26 AVR0 AIRCRAFT LIM/TEO MAL TOM - ONTARIO TECHNICAL DEPARTMENT (Aircraft) §. ~.Q.B~ 1 REPORT MO: Periodic Perfonnance Report J-4 MO. OF SHEETS----~----- TITLE: PERFORMANCE OF THE ARROW 2 PREPARED BY Perf ormance Group ~DATE . August 1958 RECOMMENDED APPROVED APPROVED FOR RELEASE CIRCULATION LIST COPIES TO : - Messrs : • FORM 1749 A-2 - 2 - J.C.Floyd R.N.Lindley J .Chamberlin C.V.Lindow F .Brame R.Marshall M.D.Willer D.Rogers M.Pesando J .Scott J.Lucas S.Kwiatkowski A.Thomann A.Buley S.Whiteley J.Hodge D.NoScard H .~acDougall J.Cohen W .B .Mccarter T.Robert's R.Rose A.Crust for R.C.A .F. (12) Performance Group (3) Library COPY No . 1 2 3 4 5 6 7 8 9 10 ll. 12 13 l4 15 16 17 18 19 20 21 22 23 - 34 35 - 37 38 • • FORM 1749 A • 2 - 3 - Summary Table 1 - Loading and Performance Figure 1 - Maximum speed 11 2 - Manoeuvrability 11 3 - Time to height 11 4 - Steady rate of climb 11 5 - Take-off distance 11 6 - Landing distance 11 7 - Acceleration at altitude a) time b) distance c) fuel II 8 - The:rmodyna.m.ic envelope II 9 - Flight envelope limitations a) 10,000 ft. b) 50,000 ft. Mission details ~ PAGE 4 5 7 8 9 10 11 12 13 14 15 16 17 18 Table 2 - Subsonic High Altitude Mission - subsonic combat 19 11 3 - Subsonic High Altitude Mission - supersonic combat 20 11 4 - Supersonic High Altitude Mission - supersonic combat II tl II II 5 - Combat Air Patrol - supernonic combat 6 - Subsonic Low Level Mission (10,000 ft.) - subsonic combat 7 - Ferry Mission (no Armament) - ventral tank ca rried throughout 8 - Ferry Mission {no Armament) - ventral tank jettisoned when empty 21 22 23 24 25 • FOAM 1749 A - 2 SUMMARY - 4 - ARRDW PERIODIC PERFORMANCE REPORT 14 PERFORMANCE OF THE ARROW 2 The performance data given in this report are ba sed on the drag and engine data given in Periodic Perforrru:mce Reports 12 and 13. They represent the best estimate of the ultimate performance of the Arrow 2 as at present evi,saged, with nominal engine nerformance of the Iroquois assumed as in :EMS 8 Issue 2. The operational weight empty used in this report is 557 lb. lighter th= the figure quoted in the August 1 weight report No. 7-0400-34 Issue 22, The principal reason for this difference is that, in this perform:mce report, no allowance has been made for the increase in engine weight included in the current weight report. The main differences bet~een this report and Periodic Performance Report No. 12 are:- 1. Revised missiqn profiles and combat weight definition, 2. The inclusion of a Thermodynamic envelope. 3. The inclusion of Flight envelope limitation curves. 4. The inclusion of acceleration performance. 5. An increase in operational weight empty of 1,489 lb. 6. Revised input data - based on flight test - for take-off and landing distances. The loading and performance data and fli ght envelope's are given in Figs. 1 to 9(b) and in Tables 1 to 8 inclusive. The Thermodynamic envelope is based on a recovery f c,ctor of 0.90, The Flight envelope limitations are based on strength and control considerations only, and do not necessarily represent the steady performance capabilities of the aircraft. It should be noted that the mission format is as agreed to at an informal meeting with the R,C.A.F. (S/L Landry, F/L Hall) but has not yet been formally approved. In the ferry mission, no consideration has been given to tail plugs, or to fuel in the weapon pack, since neither of these schemes have had formal approval for operational use, However the performance achievable with these schemes will be covered in Adden~a. This report should be considered as a draft for R.C.A,F. approval as to data presentation and mission format. If approved, it is anticipated tha t this format would comprise the basis for the WSC 1-2 perfornw.nce requirements, to which subsequent Periodic Perform.'.lnce Reports would be prepared. - ·31i,---------~- - 5 - • TABLE l - LOADING AND PERFORMANCE UNDER ICAO STANDARD A™OSPHERE CONDITIONS (Clean aircraft, i.e. no ventral tank, unless otherwise stated) Weight Operation weight empty Maximum useable internal fuel Gross Take-off weight (max.internal fuel) Combat weight ( ½ max.internal fuel weight) MaY..imum external fuel and tank lb. lb . lb. lb. (500 gallons at 7.8 lb/gall. and drop Maximum gross take-off weight (Combat mission) tank) lb . lb. t Maximum gross take-off wei ght (Ferry mission) Normal design landing gross weight Maximum landing gross weight (Combat mission) Wing loading at gross take-off weight Power loading at gross take-off weight True airspeed in level flight at combat weight Sea Level (i) Maximum thrust, A/B lit (ii) Maximum thrust, A/B unlit 50,000 ft.(i) Maximum thrust, A/B lit * Placard Speed Ceiling lb. lb. lb. lb/sq .ft. lb/l.b thrust kts. kts . kts. 46,650 19,443 66,0'93 56,372 4,242 70,335 68,607 49,783 66,093 54,0 1.52 700 ll' 665 1,147 • Ceiling at combat weight, r ate of climb 500 ft/min. with maximum thrust at optimum Mach number (1.8 M) A/B lit ft . 59,500 Rate of Climb Steady state rate of climb at combat weight Sea Level (i) Maximum thrust, A/B lit, at o.92 M (ii) Maximum thrust, A/B unlit at 527 kts. TAS • 50,000 ft. (i) Maximum Thrust, A/B lit at 1.80 M ft/min. 4?, 500 ft/min. 19,400 ft/min. 9,740 t Maximum gross take-off weight (Combat mission) less 1728 lb. missiles. • - 6 - Time to Height Time to reach 50,000 ft. and 1.5 M from engine start at gross take-off weight, maximum thrust A/B lit • Manoeuytabili ty Load factor at combat weight 1) Maximum ·thrust A/B lit 1.5 M at 50,000 ft. 2) Maxj_mum thrust A/B lit 1.8 Mat 50,000 ft. Take-off Distance Take-off distance qv~r 50 ft. obstacle at sea level at gross take-off weight J.) Maximum thrust A/B lit, standard day 2) Maximum thrust A/B unlit, standard day 3) Maximum thrust A/B lit, hot day Landing Distance Landing distance over 50 ft. obstacle at sea level at normal design landing gross wei ght Stalling Speed True stalling speed in landing configuration at combat weight at sea level Missions Combat radius of action, see mission profile for detail breakdown 1) Subsonic high altitude mission - subsonic combat 2) Subsonic high altitude mission - supersonic combat 3) Supersonic high altitude mission- supersonic combat 4) Comba t air patrol - supersonic combat 5) Subsonic low level mission (10,000 ft. ) - subsonic combat 6) Ferry Mission (no ann.ament} min. ft. ft. ft . ft, kts. n.m. n.m. n.m. n. m. nom. a) ventral tank carried throughout b) ventral tank jettisoned when empty Range n.m. Range n.m. 1.50 1.60 3,850 4,750 4,640 4,800 J.17 442 347 238 467 31+9 1,306 1,357 • ~-r -r~r 1- - 1 - r- 1 I I I \ I - -- +--- - ~ - -t I I I f- .--- __ ! -~- :- i_J • ! 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CONDITION N.M . MIN. I.B . LB ~- Start Weight - - - 66093 Engine Start - . 5 100 65993 Take-off to Unstick at S.L. Max Thrust A/B Unlit - . 3 185 65808 Acc . to 527 kts . at S.L. Max Thrust I A/B Unlit 5.0 . 88 634 65174 Climb at 527 kts. to 34,000° Max Thrust A/B Unlit (Optimum Cruise Out Alt.) 35 . 5 4.1 1765 63409 • Cruise Out at M = .91 at 34,0001 378.5 42.9 5646 57763 Climb at M = .92 to 50,0001 A/B Lit Max Thrust 23.0 2 . 65 1330 56433 Combat at M = . 92 at 50,ooon Max Thrust A/B Lit - 5.0 1620 53085 * Descend to 36,0009 at Idl~ Thrust - 2.8 210 52875 Cruise Back at M = .51 at; bptimum Altitude (36 1 000 ft. 442.0 50 . 8 5359 47516 Loiter Over Base at 36,0008 at Max Endurance speed - 15 . 0 1530 45986 Descend to S .L <> at Idle 'Thrust 6 . 2 324 45662 Land with Reserves f or 5 min. Loiter at Max. Endurance Sneed 5. 0 71.0 /.J.Q22 TOTAL 88.l. . O 1_16 .13 12ML .... 7.8 lb/gallon fuel density. llli1728 lb . of missiles fired during co:nibat . FORM 1749 A - 2 .. 20 = TABLE 3 - ARRDW,.2 WITH IROQUOIS S@ES 2 ENGINES SUBSONIC HIGH &:!:!TUDE MISSION - SUPERSONIC CO@AT DISTANCE TIME FUEL CONDITION N.M. MIN. LB. Start Weight - - - Engine Start - .5 100 Take-off to Unstick at S.L. Max Thrust A/B Unl.it - .3 l.85 Acc. to 527 kts. at S.L. Max Thrust A/B Unlit 5.0 .88 634 Climb at 527 kts. to 34,0001 Max Thrust A/B Unlit (Optiµium Cr uise Out Alt .) 35.5 4.1 1765 Cru.ise Out atilf= .91 at 34,0001 269.5 30.68 1+055 Acc . to M = l p.Q at 34,0001 Max Thrust A/B Lit . . ' .. Climb to ' 50,0001 at M = 1.5 Max Thrust 19.0 L65 1560 A/B Lit 18.0 1.25 1080 Combat at M = 1,5 at 50,0001 Max Thrust ·' A/B Lit - 5,0 3042 Descend to 36,oooa at Idle Thrust - 2.8 210 Cruise Back at M = .91 at Optimum Altitude (36 ~000 f ts ) 347,0 39.62 421.8 Loiter Over Base at 36, 0001 at Max Endurance Speed - 15,0 1530 Descend to S.L. at Idle Thrust - 6.2 324 Land 'fith Reserves for 5 min. Loiter at ,. S .L. at Max Endurance Sneed - 5.0 71..0 TOTAT 691.. .0 112~98 1q.LJ..~ Tuel density 7.~ lb/gallon. * 1728 lb . of missiles fired during combat. A/C WT. LB. 66093 65993 65808 65174 63409 59354 '. 57794 56714 51944 t 51734 47516 45986 45662 /./,Q22 ' • • - 21 - TABLE 4 - ARROW 2 WITH IROQUOIS SERIES 2 ENGINF.S SUPERSONIC HIGH ALTITUDE MISSION - SUPERSONIC Ca,1BAT CONDITION Start Weight Engine Start Take-off to unstick at S.L. Max Thrust A/B l!n).i t Acc., to M • .92 at S.L. Max Thrust A/B Unlit ' Climb at M • .92 to 301000 1 Max Thru1t A/B lit Acc. to M • 1.5 at 30,000 1 max Thrust A/B Lit . Climb at M • 1.5 to 50,000 1 Max Thrust A/B Lit (Optimum Cruise Out Alt.) Cruise out at M • 1.5 at 501000 1 Combat at M • 1.5 at 50 1000 1 Max Thrust A/B Lit Descend to 36,000 1at idle thrust Cruise back at M • .91 at optimum Alt. (361 000 ft . ) Loiter over Base at 36,000 1 at Max F.ndurance Speed Descend to S.L. at Idle Thrust Land with reserves for 5 min Loiter at Max Endurance Speed TOTAL * 1728 lb of Missiles fired during combat Fuel Density 7.8 lb/gal • SECRET DISTANCE TJME FUEL N.M. MIN. LB. - 00 ~ - .5 100 - .3 185 7.0 1.1 810 9.4 1.12 156o 17 .. 8 1.48 1680 21.5 1.53 136o 182.15 12.67 5068 - 5.o 304~ 2.8 210 237.85 27.2 283~ 1,.0 1530 6.2- 324 5.o 740 L.75.7 79.9 191,1,~ .. ORM 1748 A-2 A/C Wt. Lb. 66093 65993 65808 64998 63438 61758 6o398 55330 505cO * 50350 47516 45986 45662 44922 • • ARROW 2 TABLE 5 - COMBAT AIR PATROL - SUPERSONIC COMBAT WITH VENTRAL TANK ·-'- ':' JETTISONED AT FUEL EXHAUSTION CONDITION Start Weight Engine Start Take-off to Unstick at S .L. Max Thrust A/B Unlit Acc. to 527 ~ts o at S.L. Max Thrust A/B Unlit Climb at 527 kts. to 32,0001 Max Thrust A/B Unlit ( Optimum Cruise Out Alt .) Cruise-·aut at M = ,91 at 32,0001 Acc. to M = 1.5 at 32,0001 Max Thrust A/B Lit Climb to 50,0001 A/B Lit at M = 1.5 Max Thrust Combat at M = l.5 at 50,0001 Max Thrust A/B Lit Descend to .36,0001 at Idle Thrust Cruise Back at M = .91 at Optimum Altitude (36 J0OO f t .) Loiter Over Base at .36,0001 at Max Endurance Speed Descend to S .L ~ at Idle Thrust Land with Reserves for 5 min. Loiter at S.L . at Max Endurance Sneed TOTAL 'lllfl728 lb . missiles fired during combat Fuel density 7. 8 lb/gallon • DISTANCE TIME N.M. MIN. - - - .5 - .33 5 ,4 .93 34.0 3.9 390 . 0 44.1 18 . 0 1.5 19.5 1.38 - 5, 0 - 2.8 --" 466 . 9 53 . 8 - 15 . 0 - 6 . 2 - 5 . 0 q-:n.8 l / O.JJ, FUEL A/CWT. LB. LB. - WJJ.5 100 W235 200 70035 680 69355 1820 67535 6194 60999 1610 59389 1210 58179 3042 53049 * 210 5.3199 568.3 47516 15.30 45986 324 45662 71,,0 /./,Q22 211/,1 _____,_,--------~-, • • ARROW 2 TABLE 6 - SUBSONIC LOW LEVEL MISSION (10,0001} - SUBSONIC COMBAT CONDITION Start Wei ght Engine Start Take-off to Unstick at SoL , Max Thrust A/B Unlit Acc. to 527 kts. at S .L . Max Thrust A/B Unlit Climb to 10,000Y at 527 kts. Max Thrust A/B Unlit Cruise at M = 06 at 10,0001(/Et oCruise Sp:a: Acco to M = ,92 at 10,0001 A B Unlit Combat at M = .92 at 10,0001 Max Thrust A/B Unlit Climb to .36, 0001 at 527 kts. ~/B Unlit Cruise Back at M = . 91 at Optimum Al ti tu.de (.36 .i 000 ft.) _Laj,:t;er Over Base at .36,0001 at Max Endurance Speed Descend -eo- S.L. at Idle Thrust Land with Reserves for 5 min . Loiter at SaL . at Max Endurance Sneed TOTAL r. 1728 lbo missiles fired during combat Fuel density 7.8 lb/gallono DISTANCE NoM o - - - 5.0 5.7 .3.35 . .3 .3 .1 - 24,5 .324. 6 - - - 698.2 TIME F1JEL MIN. LB. - - .5 100 . ,3 185 . 88 6.34 .7 480 52.6 7050 . .39 220 5.0 .3220 2.8 1010 .37.,3 .3950 15.0 1530 6.2 .324 5.0 71.,,0 126.7 191.43 A/C WT. LB. 66093 -e,599.3 65808 65174 64694 57644 57424 52476 * 51466 47516 45986 45662 J.j,Q22 -------~- • FORM 1749 A -2 - 24 - ARROW 2 - IROQUOIS SERIES 2 ENGINES TABLE 7 - FERRY MISSION (NO AiMAMENT) VENTRAL TANK CARRIED THROUGHOUT DISTANCE TIME CONDITION N.M. MIN. Start Weight - - Engine Start - .50 Take-off to Unstick Max Thrust A/B Unli i - .33 Accelerate to 527 kts. at S.L. A/B Unlit 5.2 .92 Climb to 30,0001 Max Thrust A/B Unlit at 527 kts. TAS 29.0 3.37 Cruise Climb to 36,000'" at M = .91 1271.8 145,5 L9iter Over Base 15 minso at 36,0001 - 15.0 Descend to S.L . at .Idle Thrust - 6.2 Land with Reserves f or 5 mins. Loiter at SoL o at Max Endurance Speed - 5.0 TOTAL 1106.0 176.82 Fuel density 7 , 8 lb/gallon, FUEL A/CWT. LB. LB. - 68,607 100 68,507 198 68,309 662 67,647 1640 66,007 18129 47,878 1530 46,348 324 46,024 760 i,S .261,. 211/, 1 -------------~- - 25 - FORM 1749 A -2 ARROW 2 - IROQUOIS SERIES 2 ENGINES TABLE 8 - FERRY MISSION (NO ARMAMENT) ' VENTRAL TANK JETTISONED 'WHEN :EMPTY DISTANCE CONDITION N.M . Start Weight - Engine Start - Take-off to Unstick Max Thrust A/B Unlit - Accelerate to 527 kts. A/B Unlit at S.L. 5. 2 Climb to .30,'0001 Max Thrust A/B Unlit 527 kts. TAS 29.0 Cruise C~imh to .36,0001 at M = .91 1,322.6 Loiter Over Base ,15 mins. at .36,0001 - Descend to S.L. at Idle Thrust - Land with Reserves for 5 mins. Loiter at S .L. at Max Endurance Speed - TOTAL 1,356.8 Fuel density ?.8 lb/gallon. SECRET - 0:-- --- - - TIME FUEL A/CWT. MIN. LB. LB. - - 68,607 .50 100 68,507 . ,3,3 198 68,.309 .92 662 67,647 ,3.,37 1640 66.,007 151.1.3 18129 47,5.36 15.0 15.30 46,006 6.2 .324 45,682 5.0 760 U.,922 182.L.. 211/.1

Performance of the Arrow 2: periodic performance report 14

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