The case for a high-speed research airplane - Results from an in-house study

Kirkham, F. S.; Jackson, L. R.; Weidner, J. P.

doi:10.2514/6.1974-988

Cited by 3 publications

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“…6 ' 7 This research has resulted in a growing capability in vehicle synthesis along with an increasing awareness of apPresented as Paper 78-6 at the AIAA 16th Aerospace Sciences Meeting, Huntsville, Ala., Jan. 16-18, 1978; submitted May 22, 1978; revision received March 31, 1979. This paper is declared a work of the U.S. Government and therefore is in the public domain.…”

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confidence: 98%

Performance Potential and Research Needs of a Hypersonic, Airbreathing, Lifting Missile Concept

Hunt

Lawing

Marcum

et al. 1979

Journal of Aircraft

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This paper reports the results of a conceptual study to define the performance potential, scaling relationships, and research needs of a hypersonic missile concept formulated about an airframe-integrated propulsion system. A baseline missile design is developed and the rationale for selecting a heat-sink structural approach is described. Modifications to a NASA-Langley-developed fixed-geometry, modular scramjet are presented that may be required to achieve the dual-mode, "hydrocarbon-fueled" engine operational characteristics utilized in predicting missile performance potential. A heat-sink structure is shown to be a viable concept for Mach 6 missiles for ranges of up to 200 n.mi. A heat-sink structure protected by multiwall heat shields is suggested as a potentially attractive system for long-range cruise missiles. Airframe-integrated propulsion systems are shown to offer potentially large benefits for missiles that require high maneuverability. The use of the missile forebody for generating inlet precompression as well as lift and use of the afterbody as a high-expansion ratio, low-drag nozzle also offer improved missile cruise performance. It is concluded that technologies being developed for hypersonic aircraft, with appropriate modifications, also can be useful for hypersonic, airbreathing, lifting missiles. Nomenclature-angle of attack = fuel equivalence ratio p = density Subscripts c = inlet cowl t = trim 2 = first minimum

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mentioning

confidence: 98%

Performance Potential and Research Needs of a Hypersonic, Airbreathing, Lifting Missile Concept

Hunt

Lawing

Marcum

et al. 1979

Journal of Aircraft

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Propulsion Options for the Hypersonic Research Airplane

Camp

Williams

1975

Journal of Aircraft

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Conceptual study of hypersonic airbreathing missiles

Hunt

Lawing

Marcum

et al. 1978

16th Aerospace Sciences Meeting

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The purpose of this paper i s t o r e p o r t r e c e n t r e s u l t s of an in-house conceptual study t o e v a l u a t e t h e performance p o t e n t i a l and research needs of a i rbreathing hypersonic m i s s i l e s . An alkylated-borane (noncryogenic) f u e l e d , dual-mode, ramjet/scranijet propulsion system s t r u c t u r e d w i t h a Rene'41 i n l e t and a carbon-carbon combustor was assumed along w i t t l a Lockalloy heat sink f u s e l a g e s t r u c t u r e a n d b e r y llium wings and control s u r f a c e s . Performance f o r an air-launched b a s e l i n e m i s s i l e w i t h a 961 pound s t a gi n g weight containing a 100 pound payload i n d i c a t e d e x c e l l e n t long range c r u i s e , moderate a c c e l e r a t i o n and high maneuverability p o t e n t i a l . For example: a t Mach 6 c r u i s e conditions (103,000 f t . ) , c r u i s e range exceeded 700 n.m.; horizontal a c c e l e r a t i o n s of 9 g ' s a r e o b t a i n a b l e f o r Mach numbers froni 4 t o 7 a t 30,000 f e e t ; approximately 40 g thrust-equal-drag turns a r e achievable w i t h t h e b a s e l i n e concept a t f l i g h t dynamic pressures of 10,000 psf ( M = 6 , 40,000 f t . ) . ranges of t h e o r d e r of 2500 nautical miles f o r payloads of 300 pounds can be achieved with moderate s i z e n.,issile c a r r y weights (9000 l b s , ) . Aerodynami c heatina analvses i n d i c a t e t h a t unprotected heat-A s i z i n g study i n d i c a t e s t h a t Mach 6 c r u i s e t o a s s e s s t h e p o t e n t i a l of t h e technology being developed i n Langley's hypersonic R&T programs f o r a p p l i c a t i o n s t o a i r b r e a t h i n g m i s s i l e s and t o ident i f y p o t e n t i a l a r e a s f o r f u r t h e r research. The i n t e n t was t o d e f i n e a concept f o r an a i r -b r e a t hing hypersonic l i f t i n g m i s s i l e and t o determine p o t e n t i a l performance and s c a l i n g r e l a t i o n s h i p s . To s p e c i f y weight and deterinine t h e magnitude of t h e technological o b s t a c l e s , i t was necessary t o d e f i n e a t l e a s t one s t r u c t u r a l approach f o r eng i n e s , a i r f r a m e , and radomes, and t o a s s e s s ihermos t r u c t u r a l l i m i t a t i o n s . Ooeratino Mach numbers from 4 t o 9 were i n v e s t i g a t e d . Concepts w i t h ranqes from 20 t o 3500 nautical miles and payloads from 70 t o 500 pounds were s t u d i e d . Symbois A a r e a A' area a t shock p o s i t i o n C s p e c i f i c heat modulus of e l a s t i c i t y ultiiiiate t e n s i l e s t r e n g t h P ET F t u sink s t r u c t u r e s -w i t h i n t e r n a l i n s u l a t i o n a r e f e a s ib l e f o r ranges of several hundred miles. For ranges of several thousands of miles a multiwall r a d i a t i o n s h i e l d ( I n c o n e l f t i t a n i u m ) was s e l e c t e d f o r protect i o n of t h e i n t e r n a l l y i n s u l a t e d heat sink s t r u c t u r e . Research areas in propulsion, propulsion i n t eg r a t i o n , c o n f i...

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The case for a high-speed research airplane - Results from an in-house study

Cited by 3 publications

References 0 publications

Performance Potential and Research Needs of a Hypersonic, Airbreathing, Lifting Missile Concept

Performance Potential and Research Needs of a Hypersonic, Airbreathing, Lifting Missile Concept

Propulsion Options for the Hypersonic Research Airplane

Conceptual study of hypersonic airbreathing missiles

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