The work conducted by the ELORET Institute under this Cooperative Agreement includes the modeling of hypersonic propulsion systems and the evaluation of hypersonic vehicles in general and most recently hypersonic waverider vehicles. This work in hypersonics was applied to the design of a two-stage to orbit launch vehicle which was included in the NASA Access to Space Project. Additional research regarded the Oblique All-Wing (OAW) Project at NASA ARC and included detailed configuration studies of OAW transport aircraft. Finally, work on the modeling of subsonic and supersonic turbofan engines was conducted under this research program

Huynh, Loc C.

Waters, Mark H.

English

NASA Technical Reports Server

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NASA CONTRACTOR RI-_ORT
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ADVANCED VEHICLE CONCEPTS SYSTEMS
AND DESIGN ANALYSIS STUDIES
Mark H. Waters
and
Loc C. Huynh
Eloret Institute
3788 Fabian Way
Palo Alto, CA 94303
Prepared for
Ames Research Center
under Cooperative Agreement NCC2-746
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NA.SA
National Aeronautics and
Space Administration
Ames Research Center
Moffett Field, California 9403, _
(NASA-CR-195IIS) ADVANCED VEHICLE
CONCEPTS SYSTEMS AND DESIGN
ANALYSIS STUDIES Final Technicd]
Report, I Apr. 1992 - 3I Jan. I994
(Eloret Corp.) iOp
7!:!: : .... i
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N94-29721
Unclas
63/05 0003844
https://ntrs.nasa.gov/search.jsp?R=19940025218 2020-06-16T14:27:44+00:00Z
NASA CONTRACTOR REPORT
ADVANCED VEHICLE CONCEPTS SYSTEMS
AND DESIGN ANALYSIS STUDIES
Mark H. Waters
and
Loc. C. Huynh
CONTRACT NAS2-
t. Report No. 2. Government Accession No.
4, Title and Subtitle
ADVANCED VEHICLE CONCEPTS SYSTEMS
ANA DESIGN ANALYSIS STUDIES
7. Author(s]
Mark H. Waters and Loc C. Huynh
9, Performing Organization Name and Addreg
Eloret Institute
3788 Fabian Way
Palo Alto, CA 94303
12. Sponsoring Agency Name and Address
National Aeronautics and
Washington, D.C. 20456
Space Administr. ',
3. Recipient's Catalog No.
6, Report Dale
20 April, 1994
6. Performing Organization Code
8. Performing Organization Report No.
tO. Work Unit No.
1|, Contract or Grant No.
NCC2-746
13. Type of Report end Period Covered
14. Sponsoring Agency Code
15_ Supplementary Notes
Point of Contact: Mr. Mark H. Waters
c/o 237-11 NASA Ames Research Center, Moffett Field, CA 94035
16. Abstract
The work conducted by ELORET Institute under this Cooperative Agreement
includes the modeling of hypersonic propulsion systems, and the evaluation
of hypersonic vehicles in general and most recently hypersonic waverider
vehicles. This work in hypersonics was applied to the design of a two-stage
to orbit launch vehicle which was included in the NASA Access to Space Project.
Additional research regarded the Oblique All-Wing (OAW) Project at NASA Ames
and included detailed configuration studies of OAW transport aircraft. Finally,
work on the modeling of subsonic and supersonic turbofan engines was conducted
under this research program.
17. Key Woro_ (Suggested by Author(s))
hypersonic propulsion systems
hypersonic waverider vehicles
supersonic turbofan engines
oblique all-wing transport
lB. Distribution Statement
unclassified,
19. Security Clar, lif. (of this report|
unclassified
unlimited
20, Security Classif. (of this page)
unclassified
21. No. of Pages 22. Price"
"For sale by the National Technical Information Service, Springfield, Virginia 22161
Advanced Vehicle Concepts Systems
and Design Analysis Studies
Final Technical Report
for
Cooperative Agreement NCC2-746
for the period
April 1, 1992- January 31, 1994
Submitted to
National Aeronautics and Space Administration
Ames Research Center
Moffett Field, California 94035
Systems Analysis Branch
George H. Kidwell, Chief and Technical Officer
Prepared by
ELORET INSTITUTE
3788 Fabian Way
Palo Alto, CA 94303
Phone: (415) 493-4710
Telefax: (415) 424-9876
K. Heinemann, President and Grant Administrator
Mark H. Waters, Principal Investigator
Loc C. Huynh, Co-Principal Investigator
, 20 April, 1994
ABSTRACT
The objectivefor this researchprogramwasto developmoresophisticatedanalysistools
to model theaerodynamic,propulsion,andstructuralcharacteristicsof vehiclesandthe
dynamicsof vehiclesin flight. The work conductedby ELORET Institute underthis
CooperativeAgreementinch,desthe modelingof hypersonicpropulsionsystems,and the
evaluationof hypersonicvehiclesin generaland mostrecentlyhypersonicwaverider
vehicles. This work in hypersonicswasappliedto thedesignof a two-stageto orbit
launchvehiclewhich wasincludedin theNASA Access to Space Project. Additional
research regarded the Oblique All-Wing (OAW) Project at NASA Ames and included
detailed configuration studies of OAW transport aircraft. Finally, work on the modeling
of subsonic and supersonic turbofan engines was conducted under this research program.
INTRODUCTION
This research activity has been conducted at the Systems Analysis Branch at NASA Ames
Research Center and involves the preliminary design and mission evaluation of advanced
vehicle concepts. An advanced vehicle can be any aircraft or spacecraft being proposed
witilin or without NASA. The objective of the work is to conduct vehicle design and
mission studies in enough depth so that meaningful comparisons between concepts can be
madeandconclusionscanbedrawnregardingthe technicaland/oreconomicviability of a
given concept. Typically, several different vehicle concepts may be proposed for a given
mission requirement, and a study will emphasize a comparison between concepts.
The objective for this research program was to conduct a major effort in the development
of more sophisticated analysis tools to model the aerodynamic, propulsion, and structural
characteristics of the vehicles and dynamics of the vehicles in flight. The work conducted
by ELORET Institute under this Research Task included the following major topics:
Hypersonic Propulsion Modeling
Evaluation of a Hypersonic Waverider Vehicle
Evaluation of Vehicle Concepts for the NASA Access to Space Project
Oblique All-Wing (OAW) Transport Aircraft
Turbofan Engine Modeling
Propulsion Systems for High Flier Um'nanned Aircraft Designs
The following sections report on each of these research topics.
HYPERSONIC PROPULSION MODELING
The development of analytical tools for hypersonic vehicle analysis is a major effort in the
Systems Analysis Branch. Work under this Research Task has specifically supported the
development of a "Nose-To-Tail" (NTT) propulsion system model for hypersonic
aircraft. Sucha programis madedifficult becausethepropulsionsystemactually involves
theaircraft designaswell becausethevehicle forebodyservesasacompressionsurface
for thepropulsionsysteminlet, andthevehicleafterbodyservesasan expansionsurface
for thepropulsionsystemnozzle. Coupledwith this is theneedto usereal gaseffects
throughouttheanalysisto accountfor thereactivepropertiesof air and fuel-air mixturesat
high temperature.
Specificallyin this Task,programshavebeenwritten for theanalysisof thevehicle
forebodyshockfield andengineinlet, theenginecombustor,andtheenginenozzleand
vehicleafterbodywhich servesastheexpansionsurfacefor theengineexhaustgas. A
graphicsprogramdisplaysa flow pathelevationof thecompletepropulsionsystemwith
theassociatedshockfield geometry for eachcornponent.
HYPERSONICWAVERIDER VEHICLE
Under this ResearchTask,on-goingwork hassupportedthedesignand evaluationof a
broadrangeof vehicledesignsandrequirements(1,2,3). Most recently, thework has
concentratedon anoptimizedMach6 hydrocarbonfuel waveridervehicle. Waveriders
area classof hypersonicvehiclesdesignedto takefull advantageof thebow shock
generatedby thevehicleshapeto generatelift at hypersonicspeeds.The aerodynamic
shapeof sucha vehicle is extremelyimportantfor goodaerodynamicperformance,but if
other majorconsiderationsuchasstructuralweightandpropulsionsystemintegrationare
ignored,a completelyimpracticalvehiclewill result.
This ResearchTask hasbeenpartof a specificproject to optimizea hydrocarbonfueled
waveriderdesignedfor Mach6. A completesynthesisof thevehicleincludedall aspects
of thedesignandpracticalconstraints.As aresult of thisanalyticalproject, a waverider
vehiclehasbeendefined,andawind tunnelprogramis plannedto evaluatethe low speed
characteristicsof sucha vehicle.
SUPPORTFOR ACCESSTO SPACEPROJECT
An agencywide project to evaluatefl_turecandidatelaunchvehiclesto replacethespace
shuttletook placethroughoutmuchof 1993. The SystemsAnalysisBranchsupportedthe
work on this projectbeingdoneat theNASA AmesResearchCenter,andin particular
work under thisResearchProgramwasconductedto modela two stageto orbit (TSTO)
launchvehicles. The designhasa first stagehavingairbreathingpropulsionanda rocket
poweredsecondstage. The airbreathingpropulsionis a combinationof turbofanengines
and rarnjetsfueledwith liquid hydrogen. Takeoffandlandingareboth horizontal, andthe
beststagingMachnumberis approximately5. Theresultsof this work arevery
promising,and theywereincludedin thefinal reportpresentedto NASA Headquarters.
5
OBLIQUE ALL-WING (OAW) TRANSPORTAIRCRAFT
The OAW programis in its secondyearwith anultimategoalof a test in the9'x7'
supersonicwind tunnelin May, 1994. TheEloret InstitutePrincipal Investigatorof this
ResearchProgramhasactedastheCo-Leaderof this projectfrom its inceptionat NASA
Amesin June,1992. Thework involvesapproximately10peoplefrom four different
divisionsat NASA Arnesandcontractswith bothBoeingCommercialAirplane Company
andDouglasAircraft Company.
The specificwork within theSystemsAnalysisBranchinvolvesthedefinition and
evaluationof a reasonableconfigurationthatwould serveasacommercialtransport
aircraft to carry 450-500passengersover long range(nominally5000N.Mi.) at a flight
Mach numberof 1.6. The wind tunnelmodelto bebuilt will bebasedon this
configuration.
The definition andevaluationof theOAW aircraft configurationinvolvesall aspectsof
airplanedesign-- structures,weights,propulsion,aerodynamics,andairline economics.
NumerousCFD programsarebeingusedto designthewing aerodynamicshapeof the
wing, andtheresultingaerodynamicperformancealongwith theotheraspectsof the
designaremodeledin theACSYNT aircraft synthesisprogramto simulatethecomplete
6
aircraft designandmissionperformance.Two AIAA conferencepapers(4,5)havebeen
preparedandwere presentedin August, 1992. Thesepapershaveprovento bea valuable
interim stepin thedefinition of anOAW transportaircraft.
TURBOFAN ENGINE MODELING
The long term requirementfor this ResearchTaskis to providepropulsionsystem
modeling. To that endthereis a major andon-goingeffort to rnodelsubsonicand
supersonicturbofanenginesfor usein theaircraft synthesisprogramsusedin the Branch.
The mostdirectapproachis to usea cycleanalysisprogramdevelopedby anengine
manufacturerto producethebasicdata. Thesedatafor thrust, airflow, andfuel flow are
thenmodeledin a generalizedform andintegratedin to thesynthesisprograms. The
advantageof thisgeneralform is thatthedatacanbescaledto different ratedthrust sizes,
andthemodelsaresensitiveto changesin enginepressurerecoveryand non-standard ay
atmosphericconditions.
Most recently, therewasa major effort within this researchprogramto havethecapability
of a basiccycleanalysisprogramwithin theBranch. The long rangegoal is to include
enginecycleparameterssuchascompressionratio, turbine inlet temperature,andbypass
ratio aspararnetersin largescaleaircraft optimizationproblems.
7
The approach being taken is two-fold. First the well known cycle program NEP is being
used. This is the NASA Engine Program developed at NASA Lewis Research Center.
This program requires the use of fan, cornpressor, and turbine maps, and separate
programs developed by the General Electric Company for NASA Lewis are used for this
purpose. Second, a design point program is being written as part of the Research Task.
This program computes the detailed turbine cooling requirements of the engine, the
geometric flow path through the engine, and the engine weight. The flowpath is used to
estimate the weight of each engine component, but it is also important because key data
required for input to the turbine map program are generated.
PROPULSION SYSTEMS FOR HIGH FLYER AIRCRAFT DESIGNS
The development of tmmanned, high altitude aircraft is an on-going project within the
Systems Analysis Branch. These aircraft are referred to as "Platforms", and the objective
is to have a means for high altitude atmospheric sampling. The evaluation and modeling
of propulsion systems for these high altitude platforms was part of this research program,
and most recently the J75-P-13 turbojet engine has been modeled to study the effect of low
Reynolds numbers on turbojet engine performance. This is the engine currently used in
the U2C high altitude aircraft, and it is rated up to 75000 feet.
REFERENCES
1. Molvik, G.(MCAT), Bowles,J (NASA Ames),Huynh, L.(Eloret Institute),
"HydrocarbonScramjetwith AugmentedPreburning",AIAA paper92-3425.
2. Molvik, G.(MCAT), Bowles,J (NASA Ames),Huynh, L.(Eloret Institute),
"Analysisof aHypersonicResearchVehiclewith aHydrocarbonScramjet
Engine", AIAA paper93-0509.
3. Molvik, G.(MCAT), Bowles,J.(NASA Ames),Huynh, L.(Eloret Institute),
"A HypersonicResearchVehiclewith HydrocarbonScramjetPropulsion:Design
andAnalysis", AIAA paper93-5097,Munich Germany,November,1993.
4. Waters,M. (Eloret Inst.), Ardema,M. (NASA Ames),Roberts,C. (Sterling
Software),Kroo, I. (StanfordUniv.), "StructuralandAerodynamic
Considerationsfor anObliqueAll-Wing Aircraft', AIAA paper92-4220,
Hilton Head,SC, August, 1992.
5. Galloway,T., Gelhausen,P., Moore, M. (NASA Ames),Waters,M. (Eloret
Inst.), "ObliqueWing SupersonicTransportConcepts",AIAA paper92-4230,
Hilton Head,SC, August, 1992.


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