Decassifed 27maegs Auth: Doo S2rv00-1, 2 gt aaa TR-AC-47 (Unclassified) JOINT ATIC-WADC REPORT ON PROJECT SILVER BUG PROJECT NO. 9961 INTELLIGENCE WRIGHT-PATTERSON AIR FORCE BASE OHIO \ Ca js Information conflicting pertinently publication Air Technical Intelligence Cencer Wright-Patterson Air Force Base, Ohio responsibility information intelligence established intelligence collection government. information transmission revelation unauthorized prohibited AF-WP-O-21 APRIL 54 16M TSCILAICAL REPORT HO. TR-AC-47 (Unclassified) JOINT ATIC -ADU REPORT ON PROJECT SILVER SUG PROJECT HO. 9961 15 FEBRUARY 1955 Published by AIR TECHNICAL INTELLIGS WRIGHT-PATTERSON AIR FO! public.tion. aaa (25 ASSIFIED TABLE OF CONTENTS Section I. characteristics. 6.4 eS a eis ee Be we Oh a we 1 AL -Backerounds oa ie eee ele ester or a se wie ede hae BU Be ee. i B. Description of the Proposed Aircraft... 0... eee ee ee ee 1 bp WOE ROXUEDCG sites or scYorViel. a Vets daiae 5878-3, 7d: Wal, <a> capi! See? a eats Le Ly LT Section II USAF Rese-rch and Development Status. 6 ee ee ee eee 3 A. Principal Problem Areas 2... 1 ww ee ttt tt we ttt 23 B. Present Development Status... 2... 1. ee tt ete et tee 23 LIST GF ILLUSTRATIONS Figure 1 Three-view General Arrangement of Proposed Multi-engine Research Aireratt 2. 6 ee ee ee ee ee ee ew tt wt et 2 Figure 2 Cut Away of Research Aircraft .. 2... eee ee ee eee 3 Figure 3 Three-view General Arrangement of Research Aircratt ...... 5 Figure 4 Section Cutaway of Research Aircraft . 2... eee ee ee G Figure 5 Ground Cushion Effect .. 2... ce ee ee ee ee ee Bd Figure Airflow Into Intake During Take-off and landing ......46. lu Floure 7 Sectlon of Airflow Pattern for Take-orf . 2... 6 ee tee 2 Figure * Typical Section of Exhaustor Duct Showing Take-off Gas Flow .. 13 Figure 9 Section Through Rear of Aircraft at Supersonic Speed... ... aL Figure 10 Typical Cross-Section Through Engine... . 1 1 ee eee ene 15 Figure 11 Through Flow at Low Forward Speed . 2... 11 ee te te 16 Figure 12 Cross-Cection Showing Beuring Airflow . 1... 2-1. ee et eee w Figure 13 Perspective View Showing True Path of Bearing Afr ....... 19 Figure 14 Exhaust Jet Angles at Low Forward Speed .. 1. eee ee ees 20 Figure 15 Coanda Effect: High Aspect Ratio Jet Jending . ..- +2... ee 22 TABLE OF CONTENTS (Cont) Characteristics Contractor Performance development, classified presenting classified unclassified, intelligence state-of-the-art intelligence information indicating specialized Factual Data concerning supplewented inaccurate presented, Development Intelligence intelligence miegivings above-mentioned Discussion progreseive Howker-Siddley associated appearance. configuration engineering investigation particular examination performance not-too-distant notentially performance capabilities, successful development supersonic characteristics. conventional axinl-flow configuretios radial-flow accomplished eliminetes conventional aerodynamic Conclusions requirevent operations. WSCLASSIAED fundamental investigated full-scale development initiated. simplicity construction associated developments. conclusions, intelligence information personnel. collection conducting development. CHARACTERISTICS A. Background requirement requirement catastrophic vulnerability conventional conventional operational concentrations elimination. investigated, requirerents. completely helicopters, convertiplanes tail-sitters flat-risers. flat-riser horizontal tail-sitter vertically horizontal tail-sitters Aeronautical Corporation flat-riser Rolls-Royce associated performince capabilities. B. Description of the Proposed Aircraft 1. General Description designation, tail-sitter, "Plat-riger. investigation, contractor flat-riser. incorporates improvements utilization fundamental thoroughly investigated. essenticily construction radial-flow appearance conventional multi-engine develorment characteristics of the vehicle. our UNCLASS HEH Three-View Multi-Engine WMS! accitier: UNCLASSISEG UNGASSIneD ortentation determining center-line horizontal "flaterizer. vertically horizontal auxilliary flat-riser technique, auxilliory peripheral fundamentals irrespective trensition, accommodate necessary. additional milti-engine configuration investigating performance, development multi-engine operational radial-flow configuration investigate concerning 2, Airtrane radial-flow structure. serodynemic mechanical engineering unsolvable considered structural themselves production identical, foundation cowprising multi-engine complexity controlling lubricating 3. Air Intake therefore, SS WYSE Bre ee 3. Three-View General Arrangement of Research Aircraft CLASSIFIED Fig. 4 Section Cutaway of Research Aircraft (Radial Flow Engine) UNCLASSIFIED und Cushion Effect Fig. 5 Gro PHYCICAL CHARACTERISTICS UNCLASSIFIED Bedial-Flow Engine Aircraft Particulars Weight Dimensions, etc. Alverart Gross Take-off Veight Gross wing area Span (# diameter) Height over canopy Standard meen chord Aspect ratio Mean t/c ratio excluding intake Intake base area Aprroximate jet base area in forward ?licht Wing loading at wean weight of 25,000 lbs Maxiimm internal fuel Take-off vhrust/weignt ratio SLS thrust; frontal area Particulars Aircraft Hain Structure Cockpit vell and fucl tank Intake structure Main structure Outer ving and exhauster Cockpit and canopy Control shutters Control systen Power Plant Retor asseubly Stator blades, plates ang attachuents Combustion systen Air bearing assembly Extra to structure Cockpit equipment Radio and electrics Puel systen Air conditioning and oxygen Miscellaneous SERCRAPT ELPPY WEIGH? Pisposable Load AIRCRAFT GOSS TAKE-OFF WElGdr VEIGHT BREAKDO.N Radiai-Flow Engine Aircraft perimeter) (flat-risers). In forward flight, the air ecters the plenum chouber through the forward fecing air intakes In both the uprer and lever surfaces of the aircraft. Engine exhaust gases are carried around the exheuster duct and are expelled through the @nsular nozgle which is located on the upper and lower surfaces sear the periphery, ard through the backward facing nozzies which are located on both sides of the air- craft. (See Mg 9.) 4. Propulsion Systen The prcpesed pover rlant for the single-engine research vehi ally a double-sided rediel-fley turbojet engine. Uke heart of thic very large dinapeter rotor disc which utilizes cazpressor air bleed as ite only means of Lubrication. The compressor stators, diffuser, combustion tubes, and turbine nozzle guide vanes are designed as an integral pert of the airframe. The rotating element of the conventional gas turbine engine, namely, the compressor rotor, connecting shaft and turbine wheel have been rearranged to e disc configuration. The com- pressor rotor blades are mouxted vertically on the inner dise ring; the turbine waeel bledes are mounted vertically on the outer dise ring, and the connecting disc ring {8 comparable to the conventional cennecting shaft. This dise rotates on 2 double-sided air bearing mounted between the upper and lover ccmbustioa tubes. The combustion system consists of flame tubes distributed between the structural ribs of the aircraft. The engine pressure is contained between the outer skin aud the rotor bearing plates with the latter structure being mounted combustion top intakes to the first stage of the rotor and is compressed radiolly outward through six stages giving 2 normal pressure retic of 3 to 1. From the last con- let guide vanes, through the turbine wheel, and t through the extauct comic 4g the outer perimeter of the aireraft. (See Fic 1.) During forvari 1 the upper air intae ducts are closed and the Porward facing sir imtakes are oe (fee Pig 11.) Due to the radisl floyv through the encine, the compressor bleces and turbine Therefore, manufactured for the convemtion1 engise cammressors and turbines. The proposed air beering evpporting the roteting element elininates wany of mechanical approximately ing comes fron secondary air in tie combustion reyion while the suprly for ic UNCLASSIFIED JJo-ayeL 10j ULIMeT MOAT JO JJo-ayHe],