DEVEIOPMENT S6-RDZ_199s4 T//T///rED the reci,pient such persorrs connection work perforrned on behalf The transrnission, unauthorized retention, destruction, revelation tents, in any unauthorized forbidden. to cornplr instructions infraction the Canadian Secrets Act United States title 18, DEVELOPMENT Aprll,I955 USAF Contract Malton, Ontario, Approved by: Special Projects Illustration sheets report, including the Title, Engineering Projects Group 56-RDz-Lggs$ J;C. M. Frost INTRODUCTION THE DESIGN Description Perforrnance DISCUSSION OF' ACTIVITIES Theoretical Analysis F'INANCIAL DEVELOPMENT AND PRODUCTION NEW PROGRAMS Tests Prograrn Theoretical & COST FORECAST -ECR-E{tr AVRO A'RCRAFT PRO|ECI 1794 DEVELOPMENT this report scope of work is reviewed and design is explained. An outline of the contractor is building of feasibility and perforrnance potential studies for subject air- staternent to the work accornplished. stabilization and control of propulsive satisfactory handling through the whole flight take-off to supersonic flight at Supersonic calculated present design will provide superior perforrnance estirnated of contract negotiations, speed potential ceiling of over I00,000 a rnaxirnurn range with allowances Additional tests cornpletely substantiate perforrnance Developrnent production outline new prograrn scope than cotrrpleted presented (to the developrnent envisaged), accornpanying cost estirnate. rnonths in the total arnount of staternent analytical investigations deterrnine perforrnance capabilities flat vertical take-off and landing aircraftr', together with This contract is essentially feasibility configuration the minirnurn for dernon- principles a practical applicationtt. Cushion effect of rnulti-engine configuration Aircraft perforrrlance, stability and feasibility in detail the first surnrnarized interirn develop- is covered final develop- is now cornpleted. been prepared five areas, three f,urther tunnel rnodel technical surnrnary reviews ali. technical standpoint the current AVRO A'RCRAFT I'/WTTED negotiations folLowing page) jet-propelled aircraft of forrn, ernbodying a new arrangernent engine and ernploying engine developrnent task frorn interrnediate ernploying 8 srnall conventional turbo-jets radially disposed also proposed this tirne alternative developrnent Fig. I was contract period a cornprornise between the Fig. I conceived, having a superior perforrnance fan arrangernent preserving and circular with air sorrre considerable objections also gave thrust-lift efficiency the entire between skins for engine was developed under contract several rnechanical arrangernents form shown in Fig" supplanted earlier designs. relatively rninor developing rotors of Fig. 4 by cornparison with engine of Fig. l, idea of an interrnediate has been discarded and AVRO AIRCRAFT LIMITED is proceeding construction illustrated in is described PRO|ECT 1794 INTERMEDIATE CONVENTIONAL SUBSTITUTION O A'RCRA FT L'/W'7-EO AURO A'RCRAFT distinguish undertaking the aircraft LIMITED as Description diarneter; the canopyi is approxirnately in section weigh about rnaxirnurn rnaxirnurn Arrnstrong turbo_jets exhausting generators contra-rotating centrifugal irnpellers irnpellers, cornparison conventional centrifugal turbo-jets, the upper the irnpellers is d.irected thus behave statically their airintakes. IMPEIIER AND UPPER AND TOWER PILOT'S COCKPIT FUEL TANKS ENGINE INTAKE CONTROT SHUTTERS TURBINE EXHAUST VIPER 8 ENGINES IMPELTER AND TURBINEENGINE TAILPIPE PlAlI YIEW A]ID SECTTO]I THROUGH UR O IT'RCRA A VR O A'RCRA FT I, |/W'7EI' is diffusea iritfre wing where fuel the thrust, pneurnatically controlled gills (rig. it exhausts all around aircraft periphery; vertically the exhaust for rnanoeuvring stabilizing in all flight conditions, separate additional controls are not required for vertical take-off and hovering. will control shutters by rneans conventional stick control sirnilarly the other. stabilizing, the aircraft pltches Stabilization is essential centre of gravity the chord frorn leading edge, the aircraft would be stable the r/4 chord position. The change aircraft pitches sarne function as the fixed stabilizer conventional closed and shuttersf! PRO'ECT 1794 A VRO A'RCRA FT A'RCRAFT T'/W'TED bottorn are opened wide. thrust is all around the wing; however jeteround-wing configuration pro- duces a powerful is, in fact, 20 feet (Fig. cushion effect falls off the thrust augrnented arrangernent that transition frorn the By operating transition accelerate aircraft, and the thrust accelerate rise into short distance starting point, flight rarn pressure air intake which rnakes burning rrlore efficient" At supersonic augrnentation large rrrass irnpellers handle, a also leads weight ratio ceiling possible. efficiency at supersonic engine reasonable, supersonic either a vertical descent rnay be rnade, with PRO|ECT 1794 GROUilD CUSHIO]I EFFECT AVRO A'RCRAFT T'/J4'TET' augrnentation hot rnain steep approach Transition transition. is raised transferred to the undersurface and leaned forward collec- tively to falls close fully hovering condition. on sinking the throttle Perforrnance perforrnance first prototype initially be restricted restriction the Viper engines. restriction been rernoved: cornbustion ternperature, Supersonic for norrnal acceleration internal fuel) allowances take-off clirnb and acceleration, ,4'*PCRAFT 2'/14'TET' AVRO A'RCRAFT T'/W'TED NET THRUST MAIN COMBU tB. TI{RUSI THRUST IOSS F{OOOOOOOOC)OO ,noooooooooo talOOc-\OlO.tl(v)N 1794'STILL AIR PROIECT 1794 DISCUSSION ACTIVITIES A tabular Tests: A through during ln three groups irnportant tests, involving been carried scale* reflection these tests, which Massie Mernorial Wind Tunnel Developrnent was rnade illustration l5 are photographs rnodel and associated equiprnent. all phases operation, transition flight wlth 704 is slightly tunnel rnodels tested, which were an earlier thickness/chord Corrections been rnade perforrnance difference. MODEL NO.2/I6 A UPO A'RCRAFT I'/J4'TED FIG. t3 116 SCATE SUBSOI|IC A URO /A'RCRAFT PRO|ECr 1794 the large transition thrust, intake flow, ground position and angle very cornplex was required, anticipated. cornpleted has caused sorne delay production technical reports. Nurnerous irnportant were discovered or verified these tests conclusions satisfactorily controlled during through a transition or frorn forward