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Results 1 to 25 of 659

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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

GEARED-ELEVATOR FLUTTER STUDY.RUHLIN CL; DOGGETT RV JR; GREGORY RA et al.1976; IN: STRUCT. STRUCT. DYN. MATER. CONF. 17. PROC.; KING OF PRUSSIA, PA.; 1976; S.L.; AM. INST. AERONAUT. ASTRONAUT.; DA. 1976; PP. 598-607; BIBL. 5 REF.Conference Paper

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

THE ROLE OF THE NAE 5 X 5 FOOT WIND TUNNEL IN THE DEVELOPMENT OF MODERN AIRFOIL SECTIONS.OHMAN LH.1976; CANAD. AERONAUT. SPACE J.; CANADA; DA. 1976; VOL. 22; NO 1; PP. 1-22; BIBL. 33 REF.Article

UNSTEADY FLOW.1976; IN: SYMP. TRANSSONICUM. 2. INT. UNION THEOR. APPL. MECH.; GOETTINGEN; 1975; BERLIN; SPRINGER; DA. 1976; PP. 1-108; BIBL. DISSEM.Conference Paper

VIBRATIONS DU TYPE "FLUTTER" QUASI LINEAIRES DE TORSION ET DE FLEXION D'UN PROFIL D'AILEVOZNYUK AV; KRAVCHENKO VP.1975; VYCHISLIT. PRIKL. MAT., U.S.S.R.; S.S.S.R.; DA. 1975; NO 27; PP. 113-120; ABS. ANGL.; BIBL. 4 REF.Article

SIMULATION DU FLOTTEMENT AU SOL POUR LES AVIONS DE GRAND ALLONGEMENT.RAJAGOPAL P.1974; AO-CNRS-11849; FR.; DA. 1974; PP. 1-90; ABS. ANGL.; BIBL. 2 P.; (THESE DOCT.-ING.; PARIS VI)Thesis

A PRACTICAL OPTIMUM SELECTION PROCEDURE FOR A MOTIVATOR IN ACTIVE FLUTTER SUPPRESSION SYSTEM DESIGN ON AN AIRCRAFT WITH UNDERWING STORES.TURNER MR; LODGE CG.1977; A.G.A.R.D. CONF. PROC.; FR.; DA. 1977; NO 228; PP. 1-9Article

ACTIVE FLUTTER SUPPRESSION USING TRAILING-EDGE AN TAB CONTROL SURFACES.NISSIM E.1976; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1976; VOL. 14; NO 6; PP. 757-762; BIBL. 2 REF.Article

PANEL FLUTTER OPTIMIZATION BY GRADIENT PROJECTION.PIERSON BL.1975; INTERNATION. J. NUMER. METHODS ENGNG; G.B.; DA. 1975; VOL. 9; NO 2; PP. 271-296; BIBL. 1 P. 1/2Article

COMPARISON OF SUPERCRITICAL AND CONVENTIONAL WING FLUTTER CHARACTERISTICS.FARMER MG; HANSON PW.1976; IN: STRUCT. STRUCT. DYN. MATER. CONF. 17. PROC.; KING OF PRUSSIA, PA.; 1976; S.L.; AM. INST. AERONAUT. ASTRONAUT.; DA. 1976; PP. 608-614; BIBL. 4 REF.Conference Paper

FLUTTER AND GUST RESPONSE ANALYSIS OF FLEXIBLE AIRCRAFT WITH ACTIVE CONTROL.NOLL RB; MORINO L.1976; IN: STRUCT. STRUCT. DYN. MATER. CONF. 17. PROC.; KING OF PRUSSIA, PA.; 1976; S.L.; AM. INST. AERONAUT. ASTRONAUT.; DA. 1976; PP. 389-397; BIBL. 14 REF.Conference Paper

COMPARISON OF TWO TYPES OF STRUCTURAL OPTIMIZATION PROCEDURES FOR FLUTTER REQUIREMENTS.HAFTKA RT; STARNES JH JR; BARTON FW et al.1975; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1975; VOL. 13; NO 10; PP. 1333-1339; BIBL. 17 REF.Article

A PERTURBATION METHOD FOR TRANSONIC FLOWS ABOUT OSCILLATING AIRFOILS.TRACI RM; ALBANO ED; FARR JL JR et al.1975; IN: ANN. INST. AERONAUT. ASTRONAUT. 8TH FLUID PLASMA DYN. CONF.; HARTFORD, CONN.; 1975; NEW YORK; DA. 1975; VOL. 872; PP. 1-12; BIBL. 22 REF.Conference Paper

ON THE HYDRODYNAMIC FLUTTER ANOMALY.CRISP JDC; BERREEN TF.1974; IN: NOISE SHOCK VIB. CONF. PROC.; MELBOURNE; 1974; CLAYTON; NSV CONF. ORGAN. COMM.; DA. 1974; PP. 54-61; BIBL. 7 REF.Conference Paper

INSTRUMENTAL VARIABLES ALGORITHM FOR MODAL PARAMETER IDENTIFICATION IN FLUTTER TESTINGJOHNSON W; GUPTA NK.1978; A.I.A.A. J., NEW YORK; USA; DA. 1978; VOL. 16; NO 8; PP. 800-806; BIBL. 12 REF.Article

DYNAMIC RESPONSE OF LATTICE TOWER STRUCTURES TO WIND EXCITATION.ROYLES R; DAS PK.1976; J. INDUSTR. AERODYN.; NETHERL.; DA. 1976; VOL. 1; NO 3; PP. 311-312Article

EINFLUSS SCHRAEGER HINTERKRANTEN UND EINFLUSS DES EIGENGEWICHTS DER BESPANNUNG AUF DIE UMSTROEMUNG KONISCHER PARAGLEITER MIT SCHWACHER WOELBUNG IM UEBERSCHALL. = INFLUENCE DES BORDS DE FUITE OBLIQUES ET DU POIDS DU REVETEMENT SUR L'ECOULEMENT AUTOUR DES PARAPLANEURS A FAIBLE COURBURE CONIQUE EN SUPERSONIQUEWAGNER B.1976; Z. FLUGWISSENSCH.; DTSCH.; DA. 1976; VOL. 24; NO 6; PP. 329-340; ABS. ANGL. FR.; BIBL. 8 REF.Article

APPLICATION OF A RAND-DEVELOPED NON LINEAR PROGRAMMING METHOD TO FLUTTER OPTIMIZATION.PHOA YT; CHI FH.1976; COMPUTERS AND STRUCT.; G.B.; DA. 1976; VOL. 6; NO 4-5; PP. 305-312; BIBL. 3 REF.Article

FLUTTER INVESTIGATIONS ON A COMBAT AIRCRAFT WITH A COMMAND AND STABILITY AUGMENTATION SYSTEM.LOTZE A; SENSBURG O; KUHN M et al.1975; IN: AM. INST. AERONAUT. ASTRONAUT. AIRCR. SYST. TECHNOL. MEET.; LOS ANGELES; 1975; NEW YORK; A.I.A.A.; DA. 1975; VOL. 1025; PP. 1-12; BIBL. 14 REF.Conference Paper

APPLICATION OF AN ADVANCED COMPUTERIZED STRUCTURAL DESIGN SYSTEM TO AN ARROW-WING SUPERSONIC CRUISE AIRCRAFT.ROBINSON JC; YATES EC JR; TURNER MJ et al.1975; IN: AM. INST. AERONAUT. ASTRONAUT. AIRCR. SYST. TECHNOL. MEET.; LOS ANGELES; 1975; NEW YORK; A.I.A.A.; DA. 1975; VOL. 1038; PP. 1-9; H.T. 2; BIBL. 19 REF.Conference Paper

TRANSONIC BLADE FLUTTER: A SURVEY OF NEW DEVELOPMENTSPLATZER MF.1982; SHOCK VIB. DIG.; ISSN 0583-1024; USA; DA. 1982; VOL. 14; NO 7; PP. 3-8; BIBL. 30 REF.Article

APPLICATION OF TRANSONIC CODES TO FLUTTER ANALYSIS OF CONVENTIONAL AND SUPERCRITICAL AIRFOILSYANG TY; GURUSWAMY P; STRIZ AG et al.1982; J. AIRCR.; ISSN 0021-8669; USA; DA. 1982; VOL. 19; NO 3; PP. 211-220; BIBL. 2 P.Article

DETERMINATION ET MAXIMISATION DE LA CHARGE CRITIQUE D'UNE COLONNE DE HAUGER EN PRESENCE D'AMORTISSEMENT.CLAUDON JL.1978; Z. ANGEW. MATH. PHYS.; SCHWEIZ; DA. 1978; VOL. 29; NO 2; PP. 226-236; ABS. ANGL.; BIBL. 20 REF.Article

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