COMMANDE EN TEMPS REEL DU NOMBRE DE MACH DANS UNE SOUFFLERIE TRANSSONIQUE A RAFALES.GOBERT JL.1975; OFF. NATION. ET. RECH. AEROSPAT., NOTE TECH.; FR.; DA. 1975; PP. 1-66; ABS. ANGL.; BIBL. 20 REF.; (THESE DOCT. 3E CYCLE; PARIS VI; 1975)Thesis

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A VARIATIONAL FORMULATION OF THE COMPRESSIBLE THROUGHFLOW PROBLEM.OATES GC; KNIGHT CJ; CAREY GF et al.1975; IN: GAS TURBINE CONF. PROD. SHOW; HOUSTON, TEX.; 1975; NEW YORK; AM. SOC. MECH. ENG.; DA. 1975; VOL. 75-GT-32; PP. 1-8; BIBL. 7 REF.Conference Paper

EFFECTS OF REYNOLDS NUMBER ON SWEPT-WING-BODY CONFIGURATIONS WITH HIGH LIFT DEVICES AT TRANSONIC SPEEDS.ATRAGHJI E; SORENSEN H.1974; IN: 9TH CONGR. INT. COUNC. AERONAUT. SCI. PROC.; HAIFA; 1974; JERUSALEM; WEIZMANN SCI. PRESS ISR.; DA. 1974; VOL. 1; PP. 94-120; BIBL. 8 REF.Conference Paper

EIN BEITRAG ZUR WEITERENTWICKLUNG VON PULSATIONSTRIEBWERKEN = CONTRIBUTION AU PERFECTIONNEMENT DES PULSO-REACTEURSHEISE G.1973; Z. FLUGWISSENCH.; DTSCH.; DA. 1973; VOL. 21; NO 6; PP. 189-195; ABS. ANGL. FR.; BIBL. 13 REF.Serial Issue

OSCILLATION PHENOMENA OF PSEUDO-SHOCK WAVES.IKUI T; MATSUO K; NAGAI M et al.1974; BULL. J.S.M.E.; JAP.; DA. 1974; VOL. 17; NO 112; PP. 1278-1285; BIBL. 9 REF.Article

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BOUNDARY-LAYER EFFECT IN PANEL FLUTTER.GOLDSTEIN ME.1975; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1975; VOL. 13; NO 9; PP. 1247-1249; BIBL. 7 REF.Article

A THEORETICAL AND EXPERIMENTAL STUDY OF A JET STRETCHER SYSTEMBAUER RC; MATKINS EH; BAREBO RL et al.sdIN: AIAA 7TH AERODYN. TEST. CONF. PALO ALTO, CALIF., 1972; NEW YORK; AM. INST. AERONAUT. ASTRONAUT.; DA. S.D.; NO 993; PP. 1-16; BIBL. 3 REF.Conference Paper

FACTEUR DE RECUPERATION DE THERMOCOUPLES PLACES DANS UN ECOULEMENT SUBSONIQUE.LAVERRE J; PLETIN M.1976; AERONAUT. ET ASTRONAUT.; FR.; DA. 1976; NO 58; PP. 79-86; ABS. ANGL. ALLEM.; BIBL. 3 REF.Article

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ANALYSIS OF VALIDATION TEST OF THE LANGLEY PILOT TRANSONIC CRYOGENIC TUNNEL.RAY EJ; KILGORE RA; ADCOCK JB et al.1975; J. AIRCR.; U.S.A.; DA. 1975; VOL. 12; NO 6; PP. 539-544; BIBL. 4 REF.Article

REMARKS ON UNSTEADY NEWTONIAN FLOW THEORY.MAHOOD GE; HUI WH.1976; AERONAUT. QUART.; G.B.; DA. 1976; VOL. 27; NO 1; PP. 66-74; BIBL. 9 REF.Article

RESPONSE OF A CYLINDRICAL SHELL IN SUPERSONIC FLOW TO A SHOCK LOAD.DZYGADLO Z; NOWOTARSKI I; OLEJNIK A et al.1976; J. TECH. PHYS.; POLAND; DA. 1976; VOL. 17; NO 3; PP. 279-293; ABS. POL. RUSSE; BIBL. 9 REF.Article

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STUDY OF LOW-ASPECT RATIO SWEPT AND OBLIQUE WINGS.HOPKINS EJ; LEVIN AD.1975; J. AIRCR.; U.S.A.; DA. 1975; VOL. 12; NO 8; PP. 648-652; BIBL. 12 REF.Article

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INSTATIONAERE DRUCKVERTEILUNGEN AN EINEM HARMONISCH SCHWINGENDEN, GESTAFFELTEN SCHAUFELGITTER. I. ERGEBNISSE FUER INKOMPRESSIBLE STROEMUNG. = DISTRIBUTION DE PRESSION INSTATIONNAIRE DANS UNE GRILLE D'AUBES DECALEES EN OSCILLATIONS HARMONIQUES. I. RESULTATS POUR L'ECOULEMENT INCOMPRESSIBLETRIEBSTEIN H; CARSTENS V; WAGENER Y et al.1975; DTSCHE LUFT-U. RAUMFAHRT, FORSCH.-BER.; DTSCH.; DA. 1975; VOL. 75; NO 57; PP. 1-69; ABS. ANGL.; BIBL. 1 P. 1/2Article

ETUDE NUMERIQUE DE L'ECOULEMENT HYPERSONIQUE D'UN GAZ VISQUEUX ET DE L'ECOULEMENT TRANSSONIQUE D'UN GAZ IDEAL PRES D'UN CORPS DE DIMENSIONS FINIESSEVERINOV LI; BABAKOV AV.1975; CHISLEMN. METODY MEKH. SPLOSHN. SREDY; S.S.S.R.; DA. 1975; VOL. 6; NO 1; PP. 96-105; BIBL. 11 REF.Article