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Fig- 332 Aerodynamic forces and moments acting on a canard airplane.
tatcl volume ratio. As said before, the wing liftis the
whew- V:t ,,rmS l2t,hS ,}.sfth~,cwa2agee that the carjard lift is positive. rfhen. the wing
clominant
lift is given by (3.84)
Lru = W - Lc
cm drag.
cural w g}\91:t;easr;d a smalltealltriB ,ause
nusieadstoa: erwingeaclonwaredr2irtr~rcz~rishighl }iltel:~'ootshe'lownwash
Anothe,adva ~sl~atthel isthewanar9dthstt~sexpof .ts{t"f:g~
ving, it is ttaa/ll[lsthteh~;
thecanardisat lrZthgfwier,whenthecan ;7rW"':se:obnogtl;
fieldofthecanard.Tb itchingmome_,je~po.s~s~,ethat, ;vithconventional
;anosedownpitc wever,iti: :f:2mth:ctaftwit I.Another
X;9a~t,::jt~~oc\nr,W,~:7aW"eo~,~be:~sblgOs{:uations :;9sg,X,}e~ris,~:pdaucrtino~
a.,:lr;jgo,~}...denay.harat e o. better chance of recovering i
disadvanta edfio:?"wh~i\l ,~1:thiagnurationisthatapoyjSrebl~ls:ngin a
the/andingfi; ri\ll:)nngthenoseabruptlydowr
thenoselanding gaarof redcu tl,e trun-drag penaltY is the application of so-
other worcls, the static stabilitY is
Anothermethodr ,i~(SeSl~,eoX::~PotnnzUKtleTheairplaneisintentionally
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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL1(155)
