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nESEAf!Cll AIRPL1\NE STUDY PRESllJThTIOrJ

Mach 12 \"~hicle Study: I

Veh icle Concept i

'Acceleration System . Aerodynamics .

Resear.ch Engine

Structures

; . . I",

Vehicle' Summary :

Justification and Recommen­dations

C. 1-1. IVlcLc! Ian

D. E. Fottcrm,m

). R.· Henry

R. R. Howell

c. H. McLellan

J. V. Bec!wr

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RESEARCH AIRPLANE. STUDY PR[SENTATION

.-

VEHICLE CONCEPT 1J VEHICLE SUMMARY

I I

• I ,

. - - '.~ -- ._---_ .... - ..

c. H. McLellan

". "

I ,

I

" SYSTEM STUDIES OF HYPERSONIC CRUISE VEHICLES

Mi:ssion Type

colmmerCi~~ransports - - -_ I ' '. .

Rrab'e LaUnGh~:_~. _

Military --. " ,

Strike

RECCE

RECCE - Strike

- Command and Control

Logistic Transport

, Synergetic Plane Ch ..

'ICBM 2nd Stage

Intercept -

Aero Threat

Ball istic Th feat -

S~'tei 1 He Th reat

~lu mber 'of Studies I

I

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Macll Number Attractive Missions

6 - 8 , 12; X •

6 .- 10 X , .

8 - 12

X

.. X

X

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H~( PER SON I C TRA~\l SPORT ~.' '. ~:. .. I

<""";;;:~--- .. -.,

." "

·CHARACTER I STICS .:./ .

Mach Number 6 to 8

Range 5,·000 to 6,000 Miles .. -: .. . . ,

Hydrogen Fueled . ',' ." .

Low Fineness Ratio ,

I

Tu rboramje"C Powered : .. ,

Vl}inged Vehk;e

\'

!"

,PROBLEMS

structural Weight and Life. ._

Economy. "'1.' ..... , . . Fuel. Cost

. Payload Fraction . \ . , ,

Propulsion Integration

Aerodynamic Effici8;lCY

~ " . ~ .

. .

I!: II Ii II . II Iii.

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DES ! R A 13 L ERG SEA R C· H A I R P LAN E r- EAT U RES

! N DIe AT r:::D BY Nd S S iON STU DIE S I

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research scr9mjet

3 . Lifting body configuration I

4. Wihged configuration'"

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e-.. , . Tran son ic drag .. '

problem

- . High development cost

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.:. Vehicle depends on development of . engines

Low acceleration

-. Requires long test range

\ A'CCELERATOR SYSTEMS

Rocket + Scramjet

"'i Moder'ate Isp !

I I Moderate propellent density

+ No hanson i.c drag problem ,

!

. ,

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.... .. •• ~ I

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High acceleration

- Requ i res long 'test range

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All Roc\<et

Low Isp

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+ No transon ic dra9 problem

+ Minimum develop- ' ment cost

+ Veh icle independent of development of scramjet engine

High acceleration \

+ Minimum test range

SltrL!ctL!re ..

Propulsion Rocket'

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Research Engine

Fuel

Pa"load J

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, TOTAL

PRELIMINARY ~EIGHT ESTIMATE

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Cruise time" min . .

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Take-off speed, mpll

Landing speed, mpll

..

, ,

FLIGHJ CHARACTERISTICS

Lifting Body· Lifting Body. , (With S. J. Engine) , , , , ,

12,000 12,000 , , ,

:/ 120,000 to 150,000 :" ,

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HYPERSONIC RESEARCH VEHICLE DEVELOPMENT SCHEDULE

Research VeIl kle System Cor0pJrisons (MAD)

P,O()IiOli:,?V"y Can)'or" S .. ··'dies 1· .... .:1 il.r....( '" Il~ lU.

Eva! uc:Uon and Decision

Pcol iminary Engineering System Study

Structures R 8t" D

Aefcc;;'namics R&D

. .'}search Engine R &- D

Design and Constructicn Rocl<et Veh icie Scramj8t "Engine

Final System Testing Strudures Aerodynamics Resoarch EngIne

I P I ~ 1_--1

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.. ' Tile J\I\ !.l 6 "to 12 relgime is an unexplored and mil itarily important '. . • ~ Q ,. ),;1·"· "_ J"'" C". i _.J.. rt rGgl!lI(; n8GUmg 11 Iglll 11IV\.:;.J~lgctU\.Jn •.

J~',; . . ;'- . Study indicates that a research airplane capable of op3rating over"'

the M c 6 to 12 t'egime is, in generai l feasible, '~

,

The lifting body system could be ready for flight test aboutS years from project initiation.

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• Tile advanced scrap,jet research engine would require about' 2 years longer. :

I

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.,'

RESEARCH AIRP~ANE STUDY PRESENTATION ,

I !

Acceleration System Aerodynam ics . .: .

, I

- 1

D. E. Fetterman

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I '7 x /0·· 8' UNITARY: 20" VARIABLE' CONT.

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RESEARCH AIRPLANE STUDY PRESENTATION

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Research' Engine. • • • • .J. R. Henry

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Concept, Studies

• Experimental - J nlet .

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Systems and Controls;: I I.. .' .;::: . Iii

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Qual if. Engines .. l I ' ';' Ii,' I -..,.,------,..-' . . ·.i. : . 1'1

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...-\

RESEARCH AIRPLANE STUDY PRESENTATION

.Structures . .' . • • • • .. . R.: R. Howell ..

~ I, Ii II Ii Ii II II

I: Ii II II

\ • II . Ii I II Ii II Ii I, II I, I, II

I: II , ' I, I' I' I,

I: II

I: II II

I: II II II II

I: II II II II Ii I' II

Ii II II II II

II

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--~--~----------------~------ ~---

I I'

I I

LOWER ~UR'FACk , :SOTHERMS 0 1

I

V=12~OOOFPS, A~T=I~O~OOO FT, Na=3.4g

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01 ! 0

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__ --------..i.-----..:..-.-:.-------------+---I . \

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GENERAL stRu6TURAL REQUIREMENTS " . . . ,

i •

I

I

HEAT SHIELD I ,

I , , , ,

I I ,

; ,

INSULAT ION~--I ,

I I I

I I

• I

~-_----7~:~_' __ ' FUSELAGE STRUCTURE '.-.~-

.--TANK

-LIQU I D HYDROGEN (-423 0 F)

I ~. .' I ,

I

~~~-..;...' ~-TANK .INSULAT ION

, .

.-

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-CRYOGENIC TANK. THERMAL PROTECTION

, , . , SH IELD--..

PURGE SYSTEM I'

GAS APPLICATION

INSULATI9N He ~ I----~~~~~~~~~~~--------~

PURGE GAS SYSTEM

SEALED & EVAC • INSULATION

VACUUM SEALED INSULATION I SYSTEM

• i

. /

CO 2 I -~ __ ~~~~LU~~~~ __ ~ ________ ~

N2 _ I

, . , ,

VACUUM : CONCEPT:

MYLAR BAG

MULTIWA~L & :

METAL BAG ,

INTERN'AG VAC. SEALED

, , , -, , , ,

:. \

CONCEPT SMALL LARGE SYSTEM VAL I OAT ION SCALE SCALE· APPL I CAT ION

TESTS TESTS 1

I I

. ,

:1 'I,

. ii, !I,

. :i, ,1, ,I, ·1, ,II 'I 'I 'I

I' , 1'1 i,

- II' I,

II: ii,

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STRUCTURE THERMAL .PROTECTION ,",

' .

.":,

: '.' , "

. \ .. -.

" '" ,

COOLANT

ALLOY STRUCTURE ( 15000 F)

, .

TITANIUM ALLOY STRUCTruRE (450 0 F .

-INSULATION. ' I J N SU LA TI ON .

INSULATED STRUCTURE INSULA~ED & COOLED STRUCTURE

. , I'

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION . I

I

II \.:.-..,. J/....., ~d' I ~ "".- -.- :\' ',-,-p." II "' ... .,.,~. • .• ! :. :'" j

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TAIL ASSEMBLY

VERT I CAL PTA I L-' --I

-SECT I ON A-~

':HEAT SH IELD

INSULATION

" '

\ 1

I ,

, I

. ,,'I.':,.,

"

PANEL (SUPER ALLOY) I ,

CORRUGA TE 0 ~/EBS (SUPER ALLOY)

" '

..... , , .. ,. ~ .,.. NAT ION A l f~ E P. 0 N l, U T f C S I .. N D SPA C (; .. \ 0 t-' .f N I S Tf1 " T • 0 ~ I, . '._.~ ..... '~:"'.,. __ ...... .lo ~ ... j.~., ."_I'h&j.~~·;"':',,,~,,,,,,,,,,,,:,,,,~,~_w.,~ .... __ ....--..~: ....... ,,,,,,,,,~,,,~~,,,,·,,,!·,· _ ,,,,' .',.'..- -....... .-....-... _ ........ ~ ............ '4·1 ... , .. '.~~1· h .. "' ..... · .. ~"ol ,I .... I •• _~· ............. 1,/ .. ,-.,._ ••• • .. 1 .... ' ..• " ... ·,.' _ ••. ",_k .. _.;.... >, .... ~_ •• i .... t.I ............... .

'1 . .

I

I, 1 .

-----"-I

I . 11- ..... __ ... - ... __ .. _-

I . , ---

PROPULSION SYSTEM STRUCTURE .'.

INSULATION

H MAN I FOLD---1 2

--;;t::-

EXTERNAL AIRFLOW

.\

" .

H GAS' 2

FOR COOL I NG . \ . \.

I

I . ... . I ~. , ..... ~ t.An ............... __ w. __ .... _______ ......... · _____ .. NAT ION A L A E RON AUT f C SAN 0 S r l\ erA 0 !.', J N , $ r ~ ;~ T lor:

••••• ,. ._ .............. - .. _ .......... _~ .. It> .......... _ ......... _~_._ ... ___ .....:.-..-:._... ...... ~_~....i .................... ,.. ...... : ... ~ ... ,.I- ........ .':.,!., .... J, .... -~- .... ~ ....... ...

..• , ..... , , ... , •• ..., I ,. ..

STT:JCTtP..E

??JZ·j',RY STRUCTURE .;!ID T/~·;f.

(1) :·1odel Fs.'br:cat1on or.d Tests

(2) Structural l~a1ysis a~d Configuration Study

EAT SHIEL,DS

(1) Coatin3 Evaluations (Static)

(2) Envirorunental Tests (Dynarric)

(1) Conce?t E'l"aluo.tion - A:1al:t;ical

(2) Fabrication Developrr:ent Study (Passive)

(3) Test and E.Valuation

CTIYCGENIC TAZrrc;..Gr.:

(1)

(2)

(:~)

Helium Puree

(1) Ins~at:~~ Studies

(2) Co~ling Systems

P'ROPULSIO::: .sT~-X"T'J:ES

(1) Verifica~~~r. at High Heat Fl~~

(2) D~j~l~p~ent of Insulative Coatir~

..

I.

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I· Ii

STRUCTURE

Prirna.ry' Strueture and. Tank

Boat Shields and Leading Edge

.\

THERMAL PROT~!CN

Cryogenic TMko.ge

. Propulsion. Stru.c:turc

'; !

FACILITY

Structures Lab - LBO Radiant Heat ·Lnb ~ FRO

Materials Lab - LBO !3' In'ST with O2 - LRC

, LH2 ~est Fne111ty Structures Lab. - !aRC . 8' mST - LRC

HiSh Itent Flux Heater - LRC ' 8' HTS'l' with O2 - LEe

'.--."

-

STATUS

Elc1nt1ng, Part Existing

Elc1st1ng . c or F Item . FY 70

Being Designed . Erlsting Existing

Does Not Exist C o~ F Item FY 70

.)

~------~----~----~~~~~~~~----------~----~~~~ I

~ '-- - -',------,

--.' -....:....-::. '.--- -- ---.-- - - ---

'--~'-~..:.. ~ --:....-~ - -.:-~--:.--' ~--:'---'-: ~.- ~ -------

RESEARCH AIRPLANE STUDY PRESENTATION , ,

. ,

Justification and Recommendations . . . . . . . . . J. V. Becker

~- -

X-J

'RESEARCH AI RPLANE H I STORY

13.2 i

~!//c2);;i : F'TUD.Y, PROPOSAL

~J.:..: __ LEROPUREMENT

---:: " I PE:s~~-~bNS'.fR~ c= =-=:1 i;F LIgHT

"-"or'

_____ fJ~dL--____ .L.J1 J -558-11

.. IX~J5

L~F.:-xf5

~_ ___ l -- ---- -- _ IPRESENT PROPOSAL .. 'r'---~ . - . . - - - -- - -'

i

Ll_.l_U-'-_1 r40 '45

I II \50,

I1Jf '-~'I ----~

1

I I l J I I I. I I" I :, " I LJ .... .J~J I-L_I~L-! L I Ll-'~LJ~I~J -li'55- /60, "-65 ' , I,

-- 'CY-EAl{; - ' 170 i 75 :80 185

M - 1.06' 2~01 2.46 3.2 6.04 I \ / / C~ 0 c:::oco\ 0 I

X-I -IT X-lIs X-2 X~I5

0.9 0

XF-86

145

1.22 o X-3

2 0

-104

155

, , ,

,

3 0

YF12A

165 YEAR

12 o LRC

6-o FRC

4.5 (?)

0

USAF

175 185

'-( ..

RES. AI RCRAFT

RES. "PROTOTYPES"-

PROTOTYPES

8-12 (?) 6-12 (?) c:. 0

USAF TRANSPORT .

195 . 105

I

TECHNICAL JUSTIFICATIONS FOR MACH 6-12

AIR-BREATHING RESEARCH AIRPLANE

STRUCTURES

PROVIDE DESIGN EXPERIENCE FOR HIGH-TEMPERATURE LIGHTWEIGHT STRUCTURES

DEVELOP ADVANCED THERMAL PROTECTION METHODS

DEVELOP ADVANCED LEADING-EDGE STRUCTURES

PROVIDE LOADS, STRESS, DEFLECTION DATA

MAKE PANEL .FLUTTER STUDIES

DEVELOP MANUFACTUR I NG TECHNOLOGY FOR ABOVE

GENERAL FLIGHT VALIDATION OF DESIGN PROCEDURES

PROPULSIO}J

Tf:CHNICAL JUSTIFICATIONS FOR MACH 6-12 I ,

AIR-BREATHING RESEARCH AIRPLANE

.-

'--/.

PROVIDE FOCUS FOR DESIGN OF ADVANCED SCRAMJET CRUISE ENGINE (OUTGROWTH OF HRE) I

SOLVE COMPONENT INTEGRATION PROBLEMS . ..

PROVI DE ENGINE RESEARCH DATA UNDER FLIGHT CONDITIONS NOT ACHIEVABLE IN GROUND FACILITIES, INCLUDING EFFECTS OF TRANSIENTS

I , ..

PROVIDE OPERATIONAL EXPERIENCE WITH ENGINE SUBSYSTEMS ,

PROVIDE GENERAL VALIDATION:AND/OR UPGRADING OF ENGINE RAND D PROCEDURES I

DETERMINE EFFECTS OF PROPULSIVE JET ON AIRFRAME AERODYNAMICS

~ -------,-------------

AERODYNAMICS

TECHNICAL JUSTIFICATIONS FOR MACH 6-12

AIR-BREATHING RESEARCH AIRPLANE I

,

J

'-"" .

PRODUCE NATURAL FULLY TURBULENT BOUNDARY-LAYER CONDITIONS ON WING NOT CORRECTLY SIMULATED IN WIND TUNNELS. FOR THESE CONDITIONS OBTAIN UNIQUE DATA ON:

SKIN FR ICTION HEAT TRANSFER INTERFERENCE HEATI NG BOUNDARY-LAYER PROFILES SURFACE FLOW ANGLES PRESSURE DISTRIBUTIONS LIFT/DRAG RATIO STAB IE:ITY AND CONTROL

DETERMINE INLET AERODYNAMIC PERFORMANCE IN FLIGHT

DETERMINE HANDLING QUALITIES AND CONTROL REQUIREMENTS

11··- --

:--LEVEL -oF~·1 TE~HNQ_~Q9_Y I

, ... _ ... : _. -- .... - .. -.-- .. __ .. - .. ----_ ....•... _--_._--_ .. _._._--\ . RESEARCH AIRCRAFT FUNCTION -·-··-·----·.t~O_~YJA~YI~I·· ,

j \ .

.'

-----CEVE[-OF-l -I~gJ1NQtQgjl

~:~.

~DATA /

~ ~-.

~-- - -----------

~ _ SJJMULATED_ART/SR1]

~ ~GR(jUN1FBASED ART7~R'r-oN(YI . /'" - ------ ----- -----------------

.70 :

II

Ii,

.-

INTANGIBLE JUSTIFICATIONS FOR RESEARCH AIRPLANES

THEY PROV I DE:

FOCUS

DEFINITION OF THE REAL PROBLEMS AND THE UNIMPORTANT PROBLEMS

ELIMINATION OF FEARS OF THE UNKNOWN

A STIMULATED TECHNOLOGY DEVELOPMENT PROGRAM

RESEARCH GENERATED BY THE RESEARCH A I RPLANES

1950 (X-lis, X-4, 0-5581 5, F-92A)

FLIGHT-TEST RESULTS­

SUPPORTING RAND D

GENERAL RESEARCH I NSP I RED BY THE PROGRAM·

1968 (X-I5) _ I

FLIGHT-TEST RESULTS

SUPPORTING RAND D

GENERAL RESEARCH I NSP I RED BY X-I5 PROGRAM

NO. OF REPORTS

34

64

59

290

276

200+

Iii Ii III I'

Iii I

SUMMARY

1. A NEW RESEARCH AIRPLANE CANNOT BE JUSTIFIED SOLELY ON THE BASIS OF NEED FOR PARTICULAR FLIGHT DATA TO SUPPLEMENT GROUND-BASED

I

ART/ SRT. :

2. INTANGIBLE VALUES WHICH PRODUCE A "STIMULATED" TECHNOLOGY DEVELOP­MENT PROGRAM MUST BE ACCEPTED AS A PRIME JUSTIFICATION.

3. A RESEARCH AIRPLANE FOLLOWING THE X-I, 0-558-11, AND X-IS PHILOSOPHY OF DESIGN, PROC8REMENT, AND EXPLORATION OF NEW FLIGHT ENVIRONMENTS ,

WILL PROVI DE MAXIMUM INVOLVEMENT OF ADVANCED RESEARCH GROUPS AND MAXIMUM RESEAR:CH VALUES BOTH TANGIBLE AND INTANGIBLE.

I •

I , , ,-

I, .

RECOMMENDATIONS

1. INITIATE MAD COMPARATIVE STUDY AND EVALUATION OF ALL CANDIDATE VEHICLE SYSTEMS (WITH CENTER PARTICIPATION),

2. DEVELOP A TENTATIVE OART CONSENSUS ON A VEHICLE SYSTEM FOR MORE DETAILED ANAL YSI S AND DEFINITION.

3. ESTABLI SH INTER~CENTER TEAM FOR ANAL YSI S OF THE TENTATIVE SYSTEM.

4. START GIVING THE OVERALL EFFORT HIGH VISIBILITY BY A . PRESENTATION,TO NASA AND DOD TOP MANAGEMENTS IN SPRING OF 1969

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