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                        w
        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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