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EINE GRAPHISH-ANALYTISCHE METHODE ZUR BESTIMMUNG DER OPTIMUM-OPTIMORUM-FORM DES DUENNEN DELTAFLUEGELS IN UEBERSCHALLSTROEMUNG. = METHODE GRAPHO-ANALYTIQUE POUR DETERMINER LA FORME OPTIMALE DE L'AILE DELTA MINCE EN ECOULEMENT SUPERSONIQUENASTASE A.1974; REV. ROUMAINE SCI. TECH., MEC. APPL.; ROUMAN.; DA. 1974; VOL. 19; NO 1; PP. 15-35; BIBL. 7 REF.Article

ECOULEMENTS A DECOLLEMENT SUR UNE AILE CONIQUE CONCAVEKRAVETS VV; SHVETS AI.1983; IZVESTIJA AKADEMII NAUK SSSR. MEHANIKA ZIDKOSTI I GAZA; ISSN 0568-5281; SUN; DA. 1983; NO 2; PP. 83-91; BIBL. 12 REF.Article

Persistance et destruction des structures tourbillonnaires concentrées en particulier au-dessus d'ailes delta: critères angulaires de stabilité aux écoulements = Persistance and destruction of the concentrated vortical structures in particular above the delta wings: angular criterion of the stability of the flowBenkir, Mustapha; Le Ray, Michel.1990, 189 p.Thesis

NEAR-FIELD SUPERSONIC FLOW PATTERN OF SLENDER DELTA WINGS.CHAUDHURI SN; PRAHARAJ SC.1975; INTERNATION. J. ENGNG SCI.; G.B.; DA. 1975; VOL. 13; NO 9-10; PP. 889-904; BIBL. 17 REF.Article

CARACTERISTIQUES AERODYNAMIQUES DES AILES DELTA POUR DES VITESSES DE VOL SUBSONIQUEVORONIN VI; SHVETS AI.1981; IZV. AKAD. NAUK SSSR, MEH. ZIDK. GAZA; ISSN 0568-5281; SUN; DA. 1981; NO 6; PP. 104-109; BIBL. 10 REF.Article

CALCULATION OF VORTEX BREAKDOWN LOCATIONS FOR FLOW OVER DELTA WINGS.WILSON JD.1977; J. AIRCR.; U.S.A.; DA. 1977; VOL. 14; NO 10; PP. 1020-1022; BIBL. 13 REF.Article

OPTIMISATION DES STRUCTURES D'AVIONPETIAU C; LECINA G.1982; J. MEC. THEOR. APPL.; ISSN 0750-7240; FRA; DA. 1982; VOL. 1; NO 2; PP. 291-309; ABS. ENG; BIBL. 7 REF.Article

FLOWFIELD IN THE PLANE OF SYMMETRY BELOW A DELTA WING.CRAMER MS; GEORGE AR; SEEBASS AR et al.1976; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1976; VOL. 14; NO 2; PP. 212-215; BIBL. 2 REF.Article

IL PROGRAMMA USA PER LO "SPACE SHUTTLE" = LE PROGRAMME AMERICAIN POUR LA NAVETTE SPATIALEPINTI M.1973; IGEGNERE; ITAL.; DA. 1973; VOL. 48; NO 1; PP. 31-40Serial Issue

SUPERSONIC FLOW PAST A SLENDER DELTA WING. AN EXPERIMENTAL INVESTIGATION COVERING THE INCIDENCE RANGE-5O <OU= ALPHA <OU= 50O.RICHARDS IC.1976; AERONAUT. QUART.; G.B.; DA. 1976; VOL. 27; NO 2; PP. 143-153; BIBL. 15 REF.Article

ANALYSIS AND DESIGN OF STRAKE-WING CONFIGURATIONSLAMAR JE.1980; J. AIRCR.; USA; DA. 1980; VOL. 17; NO 1; PP. 20-27; BIBL. 15 REF.Article

THE AERODYNAMIC CHARACTERISTICS OF THE THIN DELTA WING FITTED WITH A CONICAL BODY IN SUPERSONIC FLOWNASTASE A; PARASCHIVOIU I.1972; REV. ROUMAINE SCI. TECH., MEC. APPL.; ROUMAN.; DA. 1972; VOL. 17; NO 5; PP. 963-989; BIBL. 7 REF.Serial Issue

CARACTERISTIQUES AERODYNAMIQUES D'AILES DELTA A VITESSE SUBSONIQUEVORONIN VI.1983; VESTNIK MOSKOVSKOGO UNIVERSITETA. SERIJA 1: MATEMATIKA, MEHANIKA; ISSN 0579-9368; SUN; DA. 1983; NO 1; PP. 89-91; ABS. ENG; BIBL. 4 REF.Article

AERODYNAMIC HEAT TRANSFER TO A HYPERSONIC RESEARCH AIRCRAFT MODEL (X-24C) AT MACH 6.LAWING PL; HUNT JL.1976; J. AIRCR.; U.S.A.; DA. 1976; VOL. 13; NO 12; PP. 1018-1020; BIBL. 5 REF.Article

THE EFFECT OF REYNOLDS NUMBER ON THE BOATTAIL DRAG OF TWO WING-BODY CONFIGURATIONS.REUBUSH DE.1975; IN: AM. INST. AERONAUT. ASTRONAUT.-SOC. AUTOMOT. ENG. PROPUL. CONF. 11; ANAHEIM, CALIF.; 1975; NEW YORK; A.I.A.A.; DA. 1975; VOL. 1294; PP. 1-7; BIBL. 18 REF.Conference Paper

SLENDER DELTA WING WITH CONICAL CAMBER.BERA RK.1974; J. AIRCR.; U.S.A.; DA. 1974; VOL. 11; NO 4; PP. 245-247; BIBL. 7 REF.Article

THIN ANTISYMMETRICAL DELTA WINGS WITH FINITE VELOCITIES AT THE LEADING EDGES.CARAFOLI E; STAICU S.1974; REV. ROUMAINE SCI. TECH., MEC. APPL.; ROUMAN.; DA. 1974; VOL. 19; NO 5; PP. 763-777; BIBL. 7 REF.Article

WEITERE UNTERSUCHUNGEN UEBER DIE WIRBELBILDUNG AN FLUEGELN MIT GEKNICKTEN VORDERKANTEN = NOUVELLES ETUDES SUR LA FORMATION D'UN TOURBILLON SUR UNE AILE A BORD D'ATTAQUE EN LIGNE BRISEEBRENNENSTUHL U; HUMMEL D.1982; Z. FLUGWISS. WELTRAUMFORSCH.; ISSN 0342-068X; DEU; DA. 1982; VOL. 6; NO 4; PP. 239-247; ABS. ENG; BIBL. 9 REF.Article

EFFECT OF LEADING-EDGE VORTEX FLAPS ON AERODYNAMIC PERFORMANCE OF DELTA WINGSSUBBA REDDY C.1981; J. AIRCR.; ISSN 0021-8669; USA; DA. 1981; VOL. 18; NO 9; PP. 796-798; BIBL. 8 REF.Article

AILES DELTA ANTISYMETRIQUES D'ORDRE SUPERIEUR EN REGIME SUPERSONIQUESTAICU S.1981; BUL. INST. POLITECH. "GHEORGHE GHEORGHIN-DEJ" BUCARESTI, MEC.; ROM; DA. 1981; VOL. 43; NO 3; PP. 11-20; ABS. RUM; BIBL. 4 REF.Article

FLOW REGIMES OVER DELTA WINGS AT SUPERSONIC AND HYPERSONIC SPEEDS.SQUIRE LC.1976; AERONAUT. QUART.; G.B.; DA. 1976; VOL. 27; NO 1; PP. 1-14; BIBL. 16 REF.Article

STREAMWISE DEVELOPMENT OF THE FLOW OVER A DELTA WINGSFORZA PM; SMORTO MJ.1981; AIAA J.; ISSN 0001-1452; USA; DA. 1981; VOL. 19; NO 7; PP. 833-834; BIBL. 7 REF.Article

MODERN CONCEPTS FOR DESIGN OF DELTA WINGS FOR SUPERSONIC AIRCRAFT OF SECOND GENERATIONNASTASE A.1979; Z. ANGEW. MATH. MECH.; DDR; DA. 1979; VOL. 59; NO 5; PP. T246-T248; BIBL. 8 REF.Article

ANTISYMMETRICALLY CAMBERED AND TORSIONED DELTA WINGS WITH FINITE VELOCITIES AT THE LEADING EDGES.CARAFOLI E; STAICU S.1975; REV. ROUMAINE SCI. TECH., MEC. APPL.; ROUMAN.; DA. 1975; VOL. 20; NO 2; PP. 163-177; BIBL. 7 REF.Article

INCREASING THE LIFT: DRAG RATIO OF A FLAT DELTA WINGMATTICK AA; STOLLERY JL.1981; AERONAUT. J.; ISSN 0001-9240; GBR; DA. 1981; VOL. 85; NO 848; PP. 379-386; BIBL. 2 REF.Article

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