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BEYOND THE BUFFET BOUNDARY = AU-DELA DE LA LIMITE DE BUFFETINGMAREY DG.1973; AERONAUT. J.; G.B.; DA. 1973; VOL. 77; NO 748; PP. 201-214; BIBL. 1 P. 1/2Serial Issue

AN OPTIMIZATION METHOD FOR THE DETERMINATION OF THE IMPORTANT FLUTTER MODESNISSIM E; LOTTATI I.1981; J. AICR.; ISSN 0021-8669; USA; DA. 1981; VOL. 18; NO 8; PP. 663-668; BIBL. 5 REF.Article

INFLUENCE DES PARAMETRES THEORIQUES DE L'ETAGE D'UN COMPRESSEUR AXIAL SUR L'AMORTISSEMENT AERODYNAMIQUE ET SUR L'AMORCAGE DU FLOTTEMENT DE FLEXION D'AUBES MOBILES DYNAMIQUES HOMOGENESGINZBURG SI.1976; PROBL. PROCHN., U.S.S.R.; S.S.S.R.; DA. 1976; NO 3; PP. 70-80; BIBL. 8 REF.Article

INFLUENCE DE FACTEURS AERODYNAMIQUES SUR L'AMORCAGE DU FLOTTEMENT DE TORSION, D'AUBES DE COMPRESSEURSTIKHONOV ND.1976; PROBL. PROCHN., U.S.S.R.; S.S.S.R.; DA. 1976; NO 3; PP. 66-69; BIBL. 8 REF.Article

L'INFLUENCE DES PARAMETRES GEOMETRIQUES D'UN PROFIL ET D'UNE GRILLE D'AUBE SUR LA VITESSE DE FLOTTEMENT CRITIQUE D'UNE GRILLE D'AUBES DE COMPRESSEURTIKHONOV ND.1974; PROBL. PROCHN., U.S.S.R.; S.S.S.R.; DA. 1974; VOL. 6; NO 8; PP. 57-62; BIBL. 6 REF.Article

L'INFLUENCE DU MATERIAU DE CONSTRUCTION DES AILETTES D'UN COMPRESSEUR AXIAL SUR LE REGIME D'APPARITION DU FLOTTEMENTNABATOVA NA; SHIPOV RA.1974; PROBL. PROCHN., U.S.S.R.; S.S.S.R.; DA. 1974; VOL. 6; NO 8; PP. 63-67; BIBL. 7 REF.Article

LES PROBLEMES D'AEROELASTICITE DES AILETTES DE TURBOMACHINESPISARENKO GS; OL'SHTEJN LE.1974; PROBL. PROCHN., U.S.S.R.; S.S.S.R.; DA. 1974; VOL. 6; NO 8; PP. 3-8; BIBL. 5 REF.Article

STALL FLUTTER AND NONLINEAR DIVERGENCE OF A TWO-DIMENSIONAL FLAT PLATE WING.DUGUNDJI; ARAVAMUDAN K.1976; R.F.M.; FR.; DA. 1976; NO. SPEC.; PP. 135-142; BIBL. 11 REF.; (AEROELASTICITE TURBOMACH. SYMP. IUTAM-ATTAG; PARIS; 1976)Conference Paper

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COMPORTEMENT DU PANNEAU D'UNE AILE EN REGIME TRANSITOIRE DANS UN ECOULEMENT GAZEUXVOL'MIR AS; PONOMAREV AT; POPYTALOV SA et al.1973; PRIKL. MAT. MEKH.; S.S.S.R.; DA. 1973; VOL. 37; NO 2; PP. 247-253; BIBL. 2 REF.Serial Issue

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A lower bound for some flutter loadsLY, B. L.Journal of sound and vibration. 1989, Vol 129, Num 3, pp 523-525, issn 0022-460XArticle

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Incorrectness of the k method for flutter calculationsPATIL, Mayuresh J; YURKOVICH, Rudolph N; HODGES, Dewey H et al.Journal of aircraft. 2004, Vol 41, Num 2, pp 402-405, issn 0021-8669, 4 p.Article

A dynamical interpretation of flutter instabilityBIGONI, D; WILLIS, J.R.International workshop on localisation and bifurcation theory for soils and rocks. 1994, pp 51-58Conference Paper

TEST OF PINES APPROXIMATE METHOD IN A FLUTTER CALCULATION FOR THE VIGGEN AIRCRAFT.STARK VJE.1977; J. AIRCR.; U.S.A.; DA. 1977; VOL. 14; NO 7; PP. 702-703; BIBL. 5 REF.Article

DESIGN STUDY OF STRUCTURAL CONCEPTS FOR AN ARROW-WING SUPERSONIC-CRUISE AIRCRAFT.SAKATA IF; DAVIS GW; ROBINSON JC et al.1975; IN: AM. INST. AERONAUT. ASTRONAUT. AIRCR. SYST. TECHNOL. MEET.; LOS ANGELES; 1975; NEW YORK; A.I.A.A.; DA. 1975; VOL. 1037; PP. 1-12; BIBL. 3 REF.Conference Paper

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