Theoretical characteristics in supersonic flow of two types of control surfaces on triangular wings Page: 2 of 21
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to UNT Digital Library by the UNT Libraries Government Documents Department.
Extracted Text
The following text was automatically extracted from the image on this page using optical character recognition software:
--- -/7_. -- - .. .. > k - .4 -- 4 . '_ --- - - . .. ' ,. . . 6.; . .
'4 7'
-- 4.- > _ - /.f ONATJTIC} _= ,.__ _
& ,-
_- 1.-FU -DAMENTAL ANDDERIVEP UNITS .
- --- - -
"- -- _ " - . .7 - , - ..." -- " -": "'- _ k ( , - I " -- _.. - . r , . , . ,
,-I -. . _ : - . - . / _ - . , . - ' ., . . " _ _ . .r , --
,--T >-, ": : -S -- "- -- _'T , ; .-m . -"- -,_ :- 4 . . .. 75 - --- _-)-" - ,,'-"
i- : -;i--. - _-L..'---A RONAUIC..-SYMBOL ."L_ .. ..
--' -L2 -,--7.)- - 1. "U -D I N -T~-:- D ERgE L. U rr . - ', , :,.
. - - -- , - -- ,, 7 , _ 7 - - . ' . , - -7 , - . - . . . -:. . - -- _ -.Smbol
Metric
"~ ~ ~ ~ --. - 2- -, :-
7-_ <'-. < - !T i --v . - "-- --t
A= bbr~e~ia.-- - - English-
1.4-. it. - -_
_ Abb evition-
net = mee= n:--- foot (; miile ft (or:mi)
Time t second second(or=hoir)~ sec (r
Fre~ weight of 1-ktilogri-m -kg weight of I:pound Ib
, -- -- .--_ - --. - - --, - . ___ _ _ _ _ _ _ _. -. . ,- - .Poer.
See 14
..--_ -- - . .' --- '
' xlors ower (metri) -~
kilometerss p g hour_
uetrsper second=-...kpk
mpso-sorepower..
.les erhour- -
,-feetper second-
'4--. 4,.t - .. _ ._L/. ERL SYMBOLS
.- - '-- " , --- -7---- ---,4 - '' - ) -". - - - ' N "-- - -- --' : -
o 31 -" o r. 2.1 0 V sec2 " -"--= - ,. .
'I 4
--- -s---. , _ - -
,, - > , - ,- ,-r .a - i er t - : I - c _ an us -. - .f. 2
-- .^_ . - - . "G. - - ' . -."ii- W _
"- '- ... - . - - o 32 l?4 < tle :- . . ".. - .. '
, .' _. . . -:. .,, . : -e - !_ . - : . :,.7 -- --- . .. _- ,
. . , . .-. ? _w . ". . , , . T > - - -- '.5 - - . - -.' . . .
_2 _ -__: :. .-> ,.'' -.- v..-2 , .- - : .- '= - _ .- s--_ -- ,,_ -
' - " "_ u / ' - k t - . -=- " '' % _ ', . ."- . " .. ,- . 2 '-.> - _
....:.&,-.-- --- mntmerta m ,%(n ae2x3s -_. 'of
_ q - - ,; / % '-_,-- -_. . "- - . .. - ' - ----\ ' ' - " -
... .~~~~ j .--.,,..-.<.. ais.f~ at n -y rp rsu,:pt. -
-. - - _ " -- " --- ,y _ - ... .-f. - . " - , _ . - - s_ - ' . . /
__ .._ , ,.. _ , q . _ o t _. < . .,_= . .&._... .. _ - _,~ ____
_d= ----.... .=-. ...-I 1 7 ofi ln -f !c s y ;, :S-" ....-_ . .7 -
: T . ---' . . I -:<. k ;. - ..... " ': .,; -.2 . . " ? .Q ,-
4p
mph=
fpsLi f
-'4/
.- '
S:. _- 7'
N-
I- --
-/
r .- '-- ,
-.4'rr- ' i
'44
-44
. - L. _ ._X_
Wi -
Density (fa~a per. unit voliiiii
-tan a d density of dry~i,0..-249f--kg-mstt 150 -O
- an ii 60 rm o ,0s-2378 lb-ft se ' -
Specific Weight of -standard" ai ,- 1.2255 kg/ or
)~ tg. 2 4 1 b c u f t ' '4 - 4>''4" _ '
2rr~ c; c -n .- : .. -""S Are 1 "3
"- - -S.. " A -ea4 ..wing _-/ - -' 4- - . A
- _:'4-4- -', . . N- / - :. --. ., -- ."".. = . ,. "+ - - "
- - - ,., 4-- . .. > /-- "- - . - i. . - -" . - , ' -
. . . . , - - . - , ... . ' - ,
Chord-1 = '-, - " -
Q'47' - b-'4-~i7'>\
' - '- - "". " - - "
D a
4"-- ... -'
K.. . - I-,. _.. _ Ind ce dug _ .,, ak lt cdefficie. nl.._ ... A&<. -.
-1_ ), 7' Ps
-- 4-' C '.- "--. -ODros-Wis0dUforceffibslute3,oeffi_.ient".C0 C'- _ '
-' N, '
--14 _- - - - . . . --. - _
.~ ., .: >.D f ---f _.rg.bouecefc n Ui} =_- c! -= -:c ,
. ~ ~ ~ , -.- fS g~~ic -- .. / .. .- - : -, , z , - ...-Z - --- ,- ..,... -
' - :- -- T -,, -.... _ L ; s: : .. . - .. . - , _ _ _ c - _-"- -. t" - "- _--
- -- - -" " -= " - ... . ... . . i- .. . - -
--~ -" " -.. - I--< n u e ,, b0uBc~ n G - _- .. ..
\+ '--- - - ) ...=-, =- - -' - ; - -- "" --2 -- -,.7 ---' "+ - " - tg . " ,. Y = . ..,
- ~ , _ , . - , -= .... ,=, .., - . ,, . . . , , . . -- -,< _ ,- - .__ I,. _;
~L . ' ., -4-7 - " -" " ' ' " ' ?:- "/ " r- - --.-
- " -.i," ----P r i -8Fg o7eee ee G . - %
.2 .. _ - : : : - : : . .c . . ' , .:_ .. -'N3f$ I # - - - . : , -? 4 - - , , - -- ' -- --
. . - ;Dii 1- , ->- ros.d~orcbue-officle. 0 ...
. u _ - e , ' -~ - .. " .= _ - ; .- - -. . - " - : _- . _. * 1 O .: - =
-- -;- _ ',_ ' - .. " _ _ - :. -- ,' , -. , .. " -. 7 - - " _ < f- '>U
.2,--'-' ' -:" -." ," .' , " - ,', / . = , " ,. " " " / - : ' " , " / " .. - " - -
. .. . . . - ,. .-_ . , - _ - , -,- .,," . " ' , . - - , . ,-:_ . ,/ _-. -- ,_ , , " > . - , . ,-_--
" -- 4
) -
4.4,-444'
: r
__. -.. 3
-:<, I:". . , . .. -,;
-. " ... ,. - ", 1 " ',; - 2
- - " - ^ - - ,
4 , - .
. , - - - '
-,-'= 2--; ,; ... :2 _. -.LICU SYLB-JLS
'14 4
4-"'. /
Angle -tfsetti ngowgs('relative to th"sline) -
S-Angp : f -stabilir seti relative tt"'thust 4
, esultalit angular velocity-" 4
R o n er p-- her_ e a.a i .-Ir dimtn-.
- sio- r= eg., ,for an rfoilof g1i -chord, -40
mphlstand-- pressure at 15 t C0, eth- corre-
s pounding Reynolds numbers 935,40 1; or for
a .aitioffil cd o mciodio':1 ps.the :orre-
sponding-Reynogds- number is6,S65,000)-
Angle of attack
Anglefdwnwash
Angle=of attack, iniite aspeetatio _
Aigle o1 attack, induced
SAngle- f attack, ab sote (measured from ero -
S liftpositio 1
- - F lig h t- a ht a. g le 4h ::- > . '4: /_ - ' : ,1-, .. - -- . - - -
4 - 4T\ '44-> -- -
4, -- " , . - >4-E- 44- , - = = -.-- - - / - -
7-,;.., Irg~f fi} :ib 6U e m as rd o e --:,_. --
-- , & iftpod io -;.- ::,; "-. ": , ;-; --- _ v. :___ : x. _- -->.-7.<"i:
. . ',. - . _ i. , ; _.Iu . , 2-2 '" -Z / '- :""-"" -- -F ig t h n ie .- :- . ..,> ; > ; - , , "
.. . , , , . '$ P .. . . : , , _ _ :- - . ,. ... . ... . . . . .,,? ----'- ... . & -- "M "':- -,'.7.- , ........-" - -. ' . - :i-
4'' ~ ~ -' :444 "444
:,, " , ,.
- 4, )2 4> 4 --,
-. " .{ /: -4 7 -_ .. - 44)4 . _- -4--- 4. -
,. - . '
1.. ,7 ,> -- . -
'K -(4
_ <1'
.3' 1--'-"444
. - r. .
- 1/4I
ILK('4
'--'4. --
--~ - ,.Si -- - - ~ '4 4., (4-
' 4- (
-. _. - . - -5 r 4 ;-
-. -- - . -. _
~-'4' 4 -
4, ivy;i.-
'-3,t
/ .. ,
-- - . "
' - !-
,. .-, .r i_~~__~~
. S
o{ , . ,, . . . --..-- .... -- . . . -
r . _ i .
i
--
. i y : 2 i \, -- t' F.--- .
'FY
", . '. . . . _ - ,
. _r ti_
;.
r
- " '_ ;
} ."
_. r
_,.-'- -.
-F. ,.
- 'FC,
C
"Z,
--.=TM
r f
t _" _S;-
.<; ._ / ..- ,,
;
_.
Upcoming Pages
Here’s what’s next.
Search Inside
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
Tucker, Warren A. & Nelson, Robert L. Theoretical characteristics in supersonic flow of two types of control surfaces on triangular wings, report, 1949; (https://digital.library.unt.edu/ark:/67531/metadc60260/m1/2/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.