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Results 1 to 25 of 1982

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SIMULATION AU SOL DU FLOTTEMENT POUR LES AVIONS DE GRAND ALLONGEMENT.PERUMAL RAJAGOPAL.1974; OFF. NATION. ET. RECH. AEROSPAT., NOTE TECH.; FR.; DA. 1974; NO 222; PP. 1-48; BIBL. 19 REF.Article

STALL FLUTTER OF A THIN AEROFOIL WITH LEADING EDGE SEPARATION.SHINOHARA K; TANAKA H; HANAMURA Y et al.1974; BULL. J.S.M.E.; JAP.; DA. 1974; VOL. 17; NO 107; PP. 578-586; BIBL. 13 REF.Article

LE CALCUL DE LA LIMITE D'APPARITION DU PHENOMENE DE FLOTTEMENT EN FLEXION DANS UNE GRILLE D'AUBE HOMOGENE, DANS L'HYPOTHESE DE L'APPROXIMATION QUASI LINEAIREGINZBURG SI.1974; PROBL. PROCHN., U.S.S.R.; S.S.S.R.; DA. 1974; VOL. 6; NO 8; PP. 46-51; BIBL. 7 REF.Article

AEROELASTIC STABILITY OF PERIODIC SYSTEMS WITH APPLICATION TO ROTOR BLADE FLUTTER.FRIEDMANN P; SILVERTHORN LJ.1974; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1974; VOL. 12; NO 11; PP. 1559-1565; BIBL. 18 REF.Article

PIPES SUPPORTED AT BOTH ENDS CANNOT FLUTTERHOLMES PJ.1978; J. APPL. MECH.; USA; DA. 1978; VOL. 45; NO 3; PP. 619-622; BIBL. 12 REF.Article

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 OF SUBSONIC POTENTIAL FLOW ON THE BUCKLING OF THIN PANELS UNDER EDGE COMPRESSION.KORNECKI A.1975; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1975; VOL. 13; NO 1; PP. 106-107; BIBL. 6 REF.Article

SECOND DERIVATIVES OF THE FLUTTER VELOCITY AND THE OPTIMIZATION OF AIRCRAFT STRUCTURESRUDISILL CS; BHATIA KG.1972; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1972; VOL. 10; NO 12; PP. 1569-1572; BIBL. 4 REF.Serial Issue

STABILITY OF CLAMPED RECTANGULAR PLATES IN UNIFORM SUBSONIC FLOWELLEN CH.1972; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1972; VOL. 10; NO 12; PP. 1716-1717; BIBL. 3 REF.Serial Issue

AN ANALYSIS OF AEROENGINE FAN FLUTTER USING TWIN ORTHOGONAL VIBRATION MODESFORD RAJ; FOORD CA.1980; J. ENGNG POWER; USA; DA. 1980; VOL. 102; NO 2; PP. 376-381; BIBL. 6 REF.Article

THE TORSIONAL FLUTTER CHARACTERISTICS OF A CANTILEVERED AIRFOIL CASCADE IN A SUPERSONIC INLET FLOW FIELD WITH A SUBSONIC AXIAL COMPONENT.FLEETER S; MCCLURE RB; SINNET GT et al.1974; IN: AM. INST. AERONAUT. ASTRONAUT. 7TH FLUID PLASMA DYN. CONF.; PALO ALTO, CALIF.; 1974; NEW YORK; A.I.A.A.; DA. 1974; VOL. 530; PP. 1-8; BIBL. 12 REF.Conference Paper

EVALUATION DE L'INFLUENCE DE QUELQUES FACTEURS AERODYNAMIQUES ET MECANIQUES SUR LA PRESSION CRITIQUE D'APPARITION DU FLOTTEMENT EN FLEXION SUR UNE COURONNE (AUBAGE) DE TURBOMACHINE AXIALEGINZBURG SI.1974; PROBL. PROCHN., U.S.S.R.; S.S.S.R.; DA. 1974; VOL. 6; NO 8; PP. 73-80; BIBL. 4 REF.Article

A NUMERICAL INTEGRATION METHOD FOR THE DETERMINATION OF FLUTTER SPEEDSBELL AJ; BROTTON DM.1973; INTERNATION. J. MECH. SCI.; G.B.; DA. 1973; VOL. 15; NO 6; PP. 473-483; BIBL. 9 REF.Serial Issue

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

FLOTTEMENT NON LINEAIRE D'UN DISQUE VISCO-ELASTIQUELARIONOV GS.1974; IZVEST. AKAD. NAUK S.S.S.R., MECH. TVERD. TELA; S.S.S.R.; DA. 1974; NO 4; PP. 95-100; BIBL. 7 REF.Article

LINEAR THEORY OF STALL FLUTTERRAGGETT JD.1973; A.I.A.A.J., NEW YORK; U.S.A.; DA. 1973; VOL. 11; NO 5; PP. 733-735; BIBL. 9 REF.Serial Issue

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

BENDING-TORSIONAL FLUTTER OF A CANTILEVERED WING CONTAINING A TIP MASS AND SUBJECTED TO A TRANSVERSE FOLLOWER FORCE.FELDT WT; HERRMANN G.1974; J. FLANKLIN INST.; U.S.A.; DA. 1974; VOL. 297; NO 6; PP. 467-478; BIBL. 14 REF.Article

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

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