AVRO AIRCRAFT LIMITED PERIODIC PERFORMANCE REPORT 15 PERFORMANCE OF THE ARROW 2 ...._ ANALYZED NOVEMBER 1958 Tf AIRCRAFT, ARROW 2 FILE NO: 72/PERF /36 TITLE: Classilicalion cancelled/ changed I< ,Vn<;.l<;J,$S:i.f;:i,~d By auth(.;rily cl. AV!_l.O _Arrow Declassi.f. ..... ~?.~.~1 . . ~ui~~a, tRuraen) k.~ .. ,,s· JAudp. lpo.h ·z;,_ 81I1J t ••• ~ •••• nt. ·•·· C.o:: Ch.ai.r.p.e r son 1ii;;;~;;1nt ..... .. DSIS . J ............ ........... . SECRET REPORT NO: Periodic Performance Report No. 15 49 NO. OF SHEETS _________ _ ANALYZED PERFORMANCE OF THE ARROW 2 PREPAREO BY Performance Group Nov. 1958 DATE ~/re 7 APPROVEO 1,L,. lr-~ APPROVED FOR RELEASE OATE ~ ~mt1/~,,j-j/ ~-------~- - 3 - INDEX PAGE SECTION 1, PERFORMANCE Summary Table 1 Figure 1 II 2 II 3 II 4 II 5 II 6 11 7 11 8 9 Loading and Performance Maximum Speed Manoeuvrability Time to Height Steady Rate of Climb Take-off Distance Landing Distance Acceleration at Altitude a) Time b) Distance c) Fuel Thermodynamic Envelope Flight Envel ope Limitations a) 10,000 feet b) 50,000 feet MISSION DETAILS Table 2 Subsonic Hi gh Altitude Mission - Subsonic 4 6 9 10 11 12 13 14 15 16 17 18 19 20 Combat 21 11 3 Subsonic High Altitude Miss ion - Supersonic Combat 22 Supersonic (1.5M) High Altitude Mission - Supersonic (1. 5M) Combat 23 Supersonic (1.8M) High Altitude Mission - Supersonic (L8M) Combat 24 II 4 11 4A. Combat Air Patrol - Supersonic Combat 25 Subsonic Low Level Mission (10,000 feet) - Subsonic Combat 26 II 5 11 6 II 7 Ferry Mission (no armament) - Ventral Tank carried throughout 27 SECTION 2 DRAG DATA Introduction Figures 10 - 13 SECTION 3 PROPULSION DATA Introduction Figures 14 - 29 FORM l 74i A-2 28 29 - 32 33 34- 49 ARROW PERIODIC PERFORMANCE REPORT 15 PERFORMANCE OF THE ARROW 2 (C.G, at 29.5% MAC) SUMMARY The performance data given in this report are based on the drag data given in Avro Report 71- 2/Aero rJata/17 (Revised Arrow drag based on preliminary flight test results) and propulsion data given in 72/Int . Aero/33 (Developed Iroquois Series 2 with 8050 maximum NH r.p.m. and developed afterburner). They represent the best estimate of the ultimate performance of the Arrow 2 as at present envisaged. The main differences between this report and Periodic Performance Report Number 14 are :- 1. Revised drag data. 2. Revised Engine data. 3. Change of fire control system and missile load to Hughes MA-1, with .MB .. l and GA~J/L~ missiles. 4. A decrease in operational weight empty of 758 lb. mainly due to (3 ) . The loading and performance data, flight envelopes, and mission profiles are given in Figures 1 to 9(b) and in Tables 1 to 7 inclusive. The Thermodynamic envelope is based on a recovery factor of 0 0 90. The Flight envelope limitations are based on strength and control considera tions only, and do not necessarily represent the steady performance capabilities of the aircraft. The Operational Weight Empty used in this report is considered to be conservative and apProximate only, as is the internal fuel load in the weapon pack. The internal fuel has been assumed to be the 19,433 lb. basic plus 2,180 lb. in the weapon pack. To allow for variations of O.W.E 0 and weapon pack fuel, the effects of 1,000 lb, reduction in operational weight empty , and an extra 1,000 lb . of fuel in the missile pack, on the combat radi i of action and ferry range are quoted in the following table:- FOAM 1749 A-2 l--------~ - 1. 2. J . JA. ... 4. 5. 6 . fl'ORM 1749 A • 2 Basic Effect of Mission Dist. 1000# extra N. M. internal (Radius) pack fuel = N.M. Subsonic high altitude mission ... subsonic combat 589 + 35 Subsonic high altit ude mis~ion - supersonic combat 506 + 35 Supersonic (1.5 M) high altitude mis sion - Supersonic (1.5M) combat 358 + 25 Supersonic (1.8 M) high altitude mission - supersonic (1 ,8 M) combat 338 + 25 Combat Air Patrol - Supersonic combat 620 + 35 Subsoni c low level mi ssion (10 , 000 1) - subsonic combat 396 + 25 Ferry Mission (no armament) ventral tank carried throughout RANGE. 1500 + 70 The ef fect on g ' s available at 50 , 000 feet and l ,. 5M of 1 ,000 lb . addi tional pack fuel is -. 015 g , and of 1 , 000 lb . decrease in o.w. E. +.OJ g. :.ifif:lrtn.. Effect of 1000#- reduction in o.w.E. - N0 M0 + 15 + 15 + 10 + 10 + 15 + 10 + JO - 6 - TABI.E 1 - LOADING AND PERFORMANCE UNDER ICAO STANDARD ATMOSPHERE CONDITIONS (Clean aircraft, i.e. no ventral tank, unless otherwise stated) \'/EIGHT Operational weight empty Maximum useable internal fuel Gross take- off weight (maximum internal fuel) Combat weight (1/2 max. internal fuel weight) Maximum external fuel and tank (500 gallons at 7.8 lb/gall. + drop tank) Maximum gross take-off weight (Combat mission) •,~ 1 Maximum gross t ake-off weight (Ferr-,1 mission) Normal design larding gross weight SPEED Maximum landing gross weight (Combat Mission) Wing l oading 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 1i: Pl acard speed lb. lb. lb. lb. lb. lb. lb. lb. lb. lb/sq. ft. lb/lb thrust Kts. Kts. Kts. ·y. t Maximum gross take- off weight (Combat Mission) less 1336 lb. missiles - ' iMOltE? FORM 1749 A • 2 45,892 21,613 67,505 56,699 4,242 71,747 70,411 49,958 67,505 55.2 1.55 700 a 630 - 7 - CEILING Ceili ng at combat weight, rate of climb 500 ft/min. with max. thrust at optimum Mach number (1.8 M) A/B Lit RATE OF CLIMB St eady state rate of climb at combat weight Sea Level 50,000 ft. (i) Maximum thrust, A/B lit, at 0.92M (ii ) Maximum thrust , A/B unlit at 527 Kts TAS (i) Maximum thrust, A/B lit at 1.8 M TIME TO HEIGHT Time to reach 50,000 ft. and 1.5 M from engine start at gross t ake- off weight , max. thrust A/B l i t ,t MANOEUVRABILITY Load factor at combat weight 1. Maximum t hrust A/B lit 1.5 Mat 50 , 000 ft. 2. Maximum thrust A/B lit 1.8 Mat 50,000 ft. TAKE- OFF DISTANCE Take- off distance over 50 ft. obstacle at sea level at gross take- off weight 1 . Maximum t hrust A/B lit , standard day ( +15°c) 2. Maximum thrust A/ B unlit, standard day(+ 15°c) J . Maximum thrust A/B lit, hot day ( + 380c) IANDING DISTANCE Landing distance over 50 ft. obstacle at sea level at normal design landing gross weight STALLING SPEED FORM 174g A - 2 True stalling speed in landing configuration at combat weight at sea level --SPSRlsQt ft. ft/min . ft/min. ft/min. min. ft. ft. ft. f t . Kts. 61,400 44,600 18,600 10,JJ0 4.8 4, 000 5, 070 4,870 5,260 ll7 - 8 - 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 (1.5 M) high altitude mission - supersonic (1.5 M) combat JA. Supersonic (1.8 M) high altitude mission - supersonic (1.8 M) combat. 4. Combat air patrol - supersonic combat n.m. n.m. n.m. n.m. 5. Subsonic l ow level mission (10,000 ft.) - subsonic combat n.m. 6. FORM 1749 A - 2 Ferry Mission (no armament) ventral t ank carried throughout Range n,m. 589 506 358 338 620 396 1,500 • - r M111- Li.~IH S PE.ED AT CoHlAr W1:~c;.1-1T I - - I (sii,021-s) l - ~ _; ___ ' I I r-- r -- +- l __ L - 1_gEER:fT1 ~ - - AG I J - ~- J F/~2 REPORT No', r - -;--- AR.QOW 2 I 1 I I •• ~--- - t I ' J t!M$ TO j./£/G,t./T / /2OQVO/S- S e,€/Eg 2 ,f="N61N£{ j -- - - FER(<>Y MISS/()A/ YFIVTRAL ,.ANK' CARte16/) TIIROt/61/()VT r No A£MAM£Nr A.r7ERBvRNER Vtv'-.dT • I 1- I I r~ r I ' /vJINIMt/,.,1 T-✓ME ro /-/ElvJIT .. 0 ~ t >Tj o -.£) ~ -~ [":. • 7 6 5 4 3 2 ARROW 2 FLIGHT ENVELOPE LIMITATIONS fl LOA]) ALTl\rUDEI ::- !,Q, P1l0 F.tET FAC jTOR I? wE1rc HTI = 'i6 , poo Lt, l~A__U IF.Rn_l\ DEFI.j,ECTIPN Ba.I '"' - 4' • I 17'~~ L rfmRM!<\.L cqiMMAND-+-» I/ J'JOMil~AL IJIMI T L _,· EJ_,_F.3IA 'T'Ol / ,L_.,.,.. DEFl,ECT~ON L)!MIT r~--~-- _y· rE.*h'·__..••=P· _L"l_ ~o~ V c .d . ro . b1c ATI '\.o . ~9c- &: ~," AB(l)VE F . D . ~ lL '=' r..l.j,tVJ-1..ljV.t.. A,?IJ '-RM- LIMIT !;;?o• r.-~•o.c~~ ' iii>-. I I !~l I l I I I I I I I I --- 0 !'-::-::•,~=t:C:,l 4 l I I I I -..I~..--.~ I ,I> .-~l n" • • . 8 IMACI-f NUMIBER 1. 2 1. 6 12 . 1 :L'. . ·1 - 1 -2 - 3 I I F~ ,-r~~t---+-j-1~~J_k I -_J_~l~~\l;i~L vVrlNl~i' LJ ¾.Ldf TT',g;:r f'"'.~l' LrM' ~ I ":=L ... _•~r---------1f-----+--- -1 -~ M~. ELEvtATOF ,I ~ I DEFJ.,ECT40N LlMIT I 1--· ._ .,:,cJ le•·.,:'.); •::, except Normal Commarrl Nominal ::"' :·• .. • tor·P-d f or eight change i,e. n-- = n x 56,000 l,l!HI Curve WNiJ Li:;n t p ·~ ---------W- - 21- ARROtl 2 WITH IROQUOIS SERIES 2 ENGINES TABLE 2 _ SUBSONIC HIGH ALTITUDE MISSION - SUBSONIC COMBAT CONDITION DISTANCE TIHE FUEL A/C WEIGHT (N.M.) (MIN.) (IB.) (IB.) Start Weight - - - 67,505 Engine Start - 0.5 100 67,405 Take-Off to Unstick at S.L. , Max, Thrust, A/B Unlit - 0.32 192 67,213 Acc. to 527 Kts. at S.L., Max. Thrust, A/B Unlit 5.0 o,85 609 66,604 Cli,ib at 527 Kts. T. A.S, to 35,000 1 l1ax. Thrust , A/B Unlit (Opt. Cruise Out Altitude) 39.5 4.55 1,910 64,694 Cruise Out at M = 0,905 at 35,000 1 526.0 60.50 7,260 57,434 Climb at M = 0,92 to 50 ,000 1 , A/B Lit, 11ax. Thrust 18,5 2.10 990 56,444 Combat at M = ,92 at 50,000 1 , Max. Thrust, A/B Lit - 5.0 1,650 53,458 li.: Cruise Back at M = 0.905 at Opt. Altitude (39,000 °) 589.0 68.o 6,623 46,835 Loiter over Base at 39,000 1 at Max. Endurance Speed - 15.0 1,250 45,585 Descend to S. L. at Idle Thrust - 4.05 204 45,381 Land with Reserves for 5 Min. Loiter at S.L. at Max. Endurance Speed - 5.0 825 44,556 TOTAL 1178.0 165.87 21,613 Fuel density - 7.8 lb./gallon 1,336 lb, missiles fired at combat iiiCiicii' FORM 1749 A - 2 -22- ARROW 2 WITH IROQUOIS SERIES 2 ENGINES TABLE 3 SUBSONIC HIGH ALTITUDE MISSION - SUPERSONIC COMBAT (1.5 M) CONDITION DIST. N. M. Start weight - Engine st-art - Take=off to unstick at sea level max. t hrust A/B unlit - Acc . to 527 kts. at sea level max. thrust A/B unlit 5.0 - Climb at 527 Kts. ?AS to 35,000 1 rnax. thrust A/B unlit (opt. cruise-out alt.) 39.5 - Cruise- out at M = 0.905 at 35,0001 435.4 ,. Acc. to 1.5M at 35,000° max, thrust A/B lit 14.1 Cl imb to 50,000' at 1 .5M max. thrust A/B lit 12.0 Combat at 1.5M at 50,000 9 rnax. thrust A/B lit - Cruise back@ M = 0.905 at optimum alt. (39,0001 ) 506.0 Loiter over base at 39,000 1 at max 0 endurance speed - Descend to sea level @ idle thrust - Land with reserves for 5 min. loiter at sea level at rnax. endurance speed - TOTAL 1012.0 Fuel density = 7.8 lb. / gallon 1 ,336 lb . missiles fired at combat TIME FUEL A/CWT. MINS LB. LB. =r:·· - 67,505 0.5 100 67,405 0.32 192 67,213 o.85 609 66,604 4.55 1910 •. 64,694 50.0 6078 58,616 1.22 1135 57,481 o.83 750 56,731 5. 0 3060 52.:;35• 58.7 5500 46 ,835 15. 0 1250 45 ,585 4. 05 204 45,381 5. 0 825 44,556 146.02 21 , 613 - 23 - TABLE 4 - ARROW 2 WITH IROQUOIS SERIES 2 ENGINES SUPERSONIC (1.5M) HIGH ALTITUDE MI SSION - SUPERSONIC (1.5M) COMBAT CONDIT:i:ON DIST. TlliE FUEL A/_C WT. N.M. MIN. LBS lb. Start wei ght. - - - 67,505 Engine start. - o.5 100 67.11405 Take-off to unstick at sea level max. thrust A/ B unlit. - 0.32 192 67.11213 Acc. to . 92 Mat S.L. Max thrust A/B unlit. 7.5 1.10 815 66.11398 Climb@ .92 M to 35.11000 1 Max thrust, A/B lit. 12.2 1.50 1,840 64.11558 Acc . to 1.5 Mat 35,000 1 Max thrust.11 A/B lit. 15.8 1.39 1,270 63 ,288 Climb @ 1. 5M to 50,000 1 Max thrus t 9 A/B lit . 14.5 0.98 86o 62,428 Cruise out@ 1.5M at 50,000 1 308.0 21.5 7,280 55.11148 Combat@ 1.5M at 50 , 000 1 Max thrust, A/B lit. - 5.o 3,060 50 .11 752 - Cruise back @ .90511 at optimmn altitude (39.11000 1) 358.o 41.4 3,917 46.11835 Loiter over base at 39.11000! at max. endurance speed. - 15.o 1,250 45,585 Descend to S.L. at idle thrust. - Land with reserves for 5 min. l oiter 4.05 204 45 ,381 at max. endurance speed at S.L. = 5.o 825 44.556 716.0 97 0 71! 21. 613 Fuel density" 7.8 l b/gallon. * 1336 lb missiles fi red at combat SECR E T FORM 1749 A 2 t--c=::-------------------W--:.... - 24- TABLE J.iA- ARROW 2 WITH IROQUOIS SERIES 2 ENGINES SUPERSO NIC (1.8M) HIGH ALTITUDE MISSIO~ - SUPERSONIC ..( l .8M) COMBAT COND1TIO N DIST. TIME FUEL A/C wr. N.M. MIN. LB. LB. Start weight - - - 67,505 Engine start - o.5 100 67,405 Take-off to unstick at· sea level max thrust, A/B unlit. - 0.32 192 67,213 Acc. to 0.92 Mat S.L. max. thrust, A/B unlit. 7.5 1.10 815 66JJ398 Climb @ 0.92 M to 35,000 1 max t hrust A/ B lit. 12.2 1. 50 1,840 64, 558 • Acc. to 1.80 M 0l 35,000 1 max thrust A/B lit. 26.0 2.0 1JJ970 62,588 Climb @ 1. 8 M to 53,000 1 max thrust A/B lit. 17.7 1.03 1,028 61, 560 Cruise out @ 1.8 M@ 53JJ000 1 partial A/B 274.6 16.0 6JJ240 55JJ320 Combat @ l.8M@53JJ000 1 max thrust A/B lit. - 5.o 3,450 50,534 ~( Cruise back at .905 Mat optimum altitude (39,000 1 ) 338 39.1 3, 699 46,835 Loiter over base at 39JJ000 1 at max. endurance speed. - 15.o 1,250 45JJ585 Descend to S.L. at idle thrust - 4. 05 204 45,381 Land with reserves for 5 min. loiter at max. endurance speed at S.L. - 5.o 825 44.556 b'7b 90.b 21.613 Fuel density~ 7.8 lb/gallon. * 1336 l b . missiles fired at combat. e i8 B lLt!!l 'i' FOAM 1749 A-2 ----- ------E~- - 25 - ARROW 2 WITH IROQUOIS SERIES- 2 ENGINES TABLE 5 COMBAT AIR PATROL - SUPERSONIC COMB AT (1 .5 M) Start Weight Engine Start CONDITION Take- off to unstick at sea level maximum thrust, A/B unlit Acc . to 527 Kts . at S. L., max thrust A/ B unlit Climb at 527 Kts . to 35,000 1 max thrust A/ 8 unlit (opt , cruise out alt.) Cruise out at 0 ,905Mat 35,000 1 i Ace, to 1.5 Mat 35,000 1 max thrust A/B lit Climb to 50,000 1 at 1,5 M, max thrust A/ B lit Combat at 50,000 1 at 1 . 5 M, max t hrust A/ B lit Cruise back at .905 M at optimum alt, (39,000 I ) Loiter over base at 39, )00 1 at max endurance speed Descend to S.L . at idle thrust Land with reserves for 5 min loiter at S.L. at max end. speed DIS'T N.M. 5.6 45 .0 541 14 .8 13 . 6 620 TIME MINS. 0,5 0,35 0.93 5.14 62 ,0 1.28 0 ,86 5.0 71.8 15.0 4.05 5.0 FUEL LB. 100 215 674 2150 7947 1180 805 3140 7023 1250 204 825 TOTAL 1240 171.91 25,513 Fuel density 7 .8 lb/gallon + 342 lb, ventral D.T. Jettisoned ' j * 1336 lb. missiles fired at combat. SFGPSF F O RM. 17 4 9 A · 2 A/CWT. LB. 71,747 71,647 71,432 70,758 68,608 60,319+ 59,139 58 ,334 53.858* 46,835 45,585 45,381 44,556 ARROW 2 WITH IROQUOIS SERIES 2 ENGINES Table 6 - SUBSONIC LOW LEVEL MISSION (10.000 1) - $UBSONIC COMBAT Start Weight Engine Start CONDITION Take- off to Unstick at S.L. Max Thrust A/B Unlit Acc . to 527 K. at S. L. Max. Thrust A/B Unlit Climb at 527 K TAS to 101 000 1 Max . Thrust A/B Unlit Cruise at M=0 , 70 at 101 000 1 (Opt. Cruise Speed) Acc. to M=0 , 92 at 101 000 1 Max. Thrust A/B Unlit Combat at M=,92 at 10 1 000 1 Max, Thrust A/B Unli t Climb to 39,000 1 at 527 KTS TAS Max. Thrust A/B Unlit Cruise back at M=0,905 at optimum Altitude (39 1 000 ft ,) Loiter over base at 39 1 000 ft . at max. endurance speed Descend to S,L, at idle thrust Land with reserves for 5 mins . Loiter at S,L. at Max , Endurance Speed TOTAL Fuel density 7,8 lb./gallon. x 1336 lb , missiles fired at combat. SflORl3'f DISTANCE N, M, 5 ,0 6,0· 381.0 4.o 30,0 366.0 792 TIME MIN. FUEL LB, 0.50 100 0 . 32 192 0,85 609 0,72 490 51,20 9280 0,43 260 5 ,0 3140 3 , 7 1240 42.4 4023 15.0 1250 4 , 05 204 5.0 825 A/CWT. LB. 67,505 67 ,405 67 , 213 66 , 604 66 , 114 52 , 098 X 50 , 858 46 , 835 45,585 45,381 44 , 556 t FORM 1749 A - 2 -27- ARROW 2 WITH IROQUOIS SERIES 2 ENGINES TABLE 7 - FERRY MISSION (NO ARMAMENT ) VENTRAL TA1"K CARRIED THROUGHOUT CO!'mITION DISTANCE TIME FU:.i:L (N. M.) (MI N.) (IB.) Start Weight - - - Engine Start - 0 .50 100 Take-Off to Unstick , Max. Thrust , A/B Unlit - 0.34 205 Acc . to 527 Kts. at S. L. , Max. Thrust, A/B Unli t 5,5 0.91 656 Cl i mb to 35,000 1 at 527 Kts. T.A.S. Hax. Thrust, A/B Unlit 4J.5 5.0 2,100 Cruise Climb t o 40, 000 1 at M= .905 1451.0 168.2 20 , 052 Loiter over Base at 40,000 1 at Max. En.iurance Speed - 15.0 1, 330 Descend to S. L. at Idle Thrust - 4.1 205 Land wi t h Reserves for 5 Mins. Loiter at S. L. at Max. Endurance Speed i - 5,0 865 TOTAL 1,500 199. 05 25,513 Fuel Density= 7;8 lb./gallon BlmHt8¥ A/C WEIGHT ( IB. ) 70,411 70,311 70,106 69,450 67, 350 47 ,298 45.~8 45,763 44,898 -28- SECTION 2 DRAG DATA The drag data used in this report are presented in the form of D/ p • W/ p vs M carpets in the following four figures, They are a a _ based on a mean e.g. position of 29.5% c. Basically, the estimated data of Periodic Performance Report Number 12 have been modified in the light of flight tests carried out on Aircraft 25202 and 25203. Aircraft 25203 was partially instrumented for performance flight testing, and carried out some preliminary performance tests. In view of the approximate nature of the tests, a conservative view was maintained.whilst analysing the results, and the drag reductions claimed are considered to be the minimum as evidenced by the tests. 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J. , ,t - E°• i-YA,'ToA. l- 11tt11' - I r J_j ~;\J _ _. _J _:_j __ - I 0 I o - 'II 0 0 • SECTION 3 PROPULSION DATA Introduction The chan~es within the Arrow 2/Iroquois propulsion system between publication of P. P.R. 14 and P. P.R. 15 are: - (a) A decrease in maximum high pressure rotor speed from 8150 to 8050 r.p.m. but with identical rotor swallowing capacity. (b) The introduction of a high pressure rotor control rather than a low pressure rotor control such that at free stream total temperatures greater than 288°K ther e is a drop in low pressure rotor speeds. Thus above M = 1.278 above the tropopause there is a drop inengine swallowing capacity. (c) A reduction in the variable restrictor flow area in the closed position to give small improvements in subsonic performance and significant improvements in distortion levels • Both reports contain identical intake and ejector geometry, afterburner fuel schedule, and afterburner efficiency. Prepared by Internal Aero. Group - Nov. 1958. 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Signature. ..... . . . ... .. . ........ ... •·, ··· -C·o--Cha irperson Unit / Rank / Appointmen ·········-·· ..... DSIS····3--·-... •--·"'----

Performance of the Arrow 2: periodic performance report no. 15

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