SWING WING. MODIFICATIONS IN VARIABLE GEOMETRY CONFIGURATION CONCEPTS = L'AILE PIVOTANTE. MODIFICATIONS DANS LES CONCEPTS DE CONFIGURATIONS A GEOMETRIE VARIABLEBIRD WJ.1973; AIRCR. ENGNG; G.B.; DA. 1973; VOL. 45; NO 3; PP. 12-16 (4 P.)Serial Issue

METHODE APPROCHEE POUR LE CALCUL DES CARACTERISTIQUES AERODYNAMIQUES DES AILES SEMI-ANNULAIRES A FLECHE CONSTANTE LE LONG DE L'ENVERGUREPASTUKHOV AI; KUDRYAVTSEV GS.1975; IZVEST. VYSSH. UCHEBN. ZAVED., AVIAC. TEKH.; S.S.S.R.; DA. 1975; VOL. 18; NO 2; PP. 106-111; BIBL. 1 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

AN ALTERNATIVE TREATMENT OF BOUNDARY CONDITIONS FOR THE FLOW OVER THICK WINGS.NIXON D.1977; AERONAUT. QUART.; G.B.; DA. 1977; VOL. 28; NO 2; PP. 90-96; BIBL. 15 REF.Article

ECOULEMENT SUR LES SURFACES INFERIEURES DES AILES EN V EN REGIMES DESADAPTES POUR DES NOMBRES DE MACH, INFERIEURS A CELUI DU CALCULGUN'KO YU P; MAZHUL II.1977; IZVEST. SIBIR. OTDEL. AKAD. NAUK S.S.S.R., TEKH NAUK; S.S.S.R.; DA. 1977; NO 3 PART. 1; PP. 8-12; BIBL. 8 REF.Article

A NOTE ON "LIFTING THREE-DIMENSIONAL WINGS IN TRANSONIC FLOW" BY M. S. CRAMERCRAMER MS.1981; J. FLUID MECH.; ISSN 0022-1120; GBR; DA. 1981; VOL. 109; PP. 257-258; BIBL. 3 REF.Article

LOAD DISTRIBUTIONS ON SLENDER DELTA WINGS HAVING VORTEX FLOW.KUHLMAN J.1977; J. AIRCR.; U.S.A.; DA. 1977; VOL. 14; NO 7; PP. 699-702; BIBL. 8 REF.Article

THE FLOW OVER A "HIGH" ASPECT RATIO GOTHIC WING AT SUPERSONIC SPEEDS.YEGNA NARAYAN K.1975; AERONAUT. QUART.; G.B.; DA. 1975; VOL. 26; NO 3; PP. 189-201; BIBL. 10 REF.Article

THE ROLE OF THE NAE 5-FOOT X 5-FOOT WIND TUNNEL IN THE DEVELOPMENT OF MODERN AIRFOIL SECTIONS.OHMAN LH.1975; QUART. BULL. DIV. MECH. ENGNG NATION. AERONAUT. ESTABL.; CANADA; DA. 1975; NO 3; PP. 1-39; BIBL. 2 P. 1/2Article

LIFT AND MOMENT FLUCTUATIONS OF A CAMBERED ACROFOIL UNDER NONCONVECTING STREAMWISE GUST.RAO SSP; MUKHOPADHYAY V; RAO JS et al.1977; AERONAUT. J.; G.B.; DA. 1977; VOL. 81; NO 794; PP. 83-87; BIBL. 8 REF.Article

SPANWISE CAMBERED DELTA WING WITH LEADING-EDGE SEPARATION.FERNANDEZ J; HOLLA VS.1977; J. AIRCR.; U.S.A.; DA. 1977; VOL. 14; NO 3; PP. 276-282; BIBL. 14 REF.Article

AERODYNAMIC CHARACTERISTICS OF A RECTANGULAR WING WITH A TIP CLEARANCE IN A CHANNEL.SUGIYAMA Y.1977; J. APPL. MECH.; U.S.A.; DA. 1977; VOL. 44; NO 4; PP. 541-547; BIBL. 8 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

ZUR THEORIE DER VERAENDERLICHEN TRAGFLUEGELPFEILUNG. = THEORIE DE L'AILE A GEOMETRIE VARIABLEKORDIK EJT.1974; OESTERR. INGR-Z.; OESTERR.; DA. 1974; VOL. 17; NO 12; PP. 418-427; BIBL. 14 REF.Article

CALCUL DU FLUAGE D'UNE AILE A PAROIS MINCES SUR LA BASE DE L'ANALOGIE PLANESHATAEV VG.1972; IZVEST. VYSSH. UCHEBN. ZAVED., AVIAC. TEKH.; S.S.S.R.; DA. 1972; NO 4; PP. 67-72; BIBL. 7 REF.Serial Issue

REMARKS ON APPROXIMATE CONFORMAL REPRESENTATION OF BIPLANE WING SECTIONS.PROSNAK WJ.1975; BULL. ACAD. POLON. SCI., SCI. TECH.; POLOGNE; DA. 1975; VOL. 23; NO 2; PP. 161-173; ABS. RUSSE; BIBL. 2 REF.Article

ENTWURF UEBERKRISTISCHER PROFILE MIT HILFE DER RHEOELEKTRISCHEN ANALOGIE. = PROJET DE PROFILS SUPER-CRITIQUES A L'AIDE DE L'ANALOGIE RHEOELECTRIQUESOBIECZKY H.1975; DTSCHE LUFT-U. RAUMFAHRT, FORSCH.-BER.; DTSCH.; DA. 1975; VOL. 75; NO 43; PP. 1-51; ABS. ANGL.; BIBL. 2 P.Article

ETUDE EXPERIMENTALE DES AILES NON PLANES AUX VITESSES SUPERSONIQUESBRODETSKIJ MD; KOSHCHEEV AB; CHEREMUKHIN GA et al.1974; IZVEST. SIBIR. OTDEL. AKAD. NAUK S.S.S.R., TEKH. NAUK; S.S.S.R.; DA. 1974; NO 3; PP. 33-39; BIBL. 3 REF.Article

Experimental aeroelastic behavior of unswept and forward-swept cantilever graphite/epoxy wingsLANDSBERGER, B. J; DUGUNDJI, J.Journal of aircraft. 1985, Vol 22, Num 8, pp 679-686, issn 0021-8669Article

Roller furled Genoa and rigid surface wingsail, a flexible practical wind-assist system for commercial vesselsASKER, G. C. F.Journal of wind engineering and industrial aerodynamics. 1985, Vol 20, Num 1-3, pp 61-81, issn 0167-6105Article

ANWENDUNG UND VERGLEICH MODALER PERTURBATIONSMETHODEN UND MODALER KORREKTURVERFAHREN AM BEISPIEL EINES PFEILFLUEGELS MIT ZWEI PYLONAUSSENLASTEN. = MODIFICATIONS DE STRUCTURE D'UNE MAQUETTE D'AILE FLECHE A DEUX CHARGES EXTERIEURES AU MOYEN DES METHODES DE PERTURBATIONS MODALES ET DE CORRECTIONS MODALESFREYMANN R.1977; DTSCHE LUFT- U. RAUMFAHRT, FORSCH.-BER.; DTSCH.; DA. 1977; VOL. 77; NO 21; PP. 1-43; ABS. ANGL.; BIBL. 7 REF.Serial Issue

ETUDE EXPERIMENTALE DE LA RESISTANCE DES AILES AUX VITESSES SUPERSONIQUESBRODETSKIJ MD; KOSORYGIN VS; RAFAEHLYANTS AA et al.1977; IZVEST. SIBIR. OTDEL. AKAD. NAUK S.S.S.R., TEKH. NAUK; S.S.S.R.; DA. 1977; NO 2; PP. 47-53; BIBL. 8 REF.Article

LIFT COEFFICIENTS ON A SUPERCAVITATING JET-FLAPPED FOIL BETWEEN RIGID WALLS.KIDA T; MIYAI Y.1975; BULL. J.S.M.E.; JAP.; DA. 1975; VOL. 18; NO 116; PP. 151-158; BIBL. 7 REF.Article

A STATE-OF-THE ART SURVEY OF TWO-DIMENSIONAL AIRFOIL DATA.PROUTY RW.1975; J. AMER. HELICOPTER SOC.; U.S.A.; DA. 1975; VOL. 20; NO 4; PP. 14-25; BIBL. 32 REF.Article

CALCULATION OF FORCES ON STORES IN THE VICINITY OF AIRCRAFT = CALCUL DES FORCES S'EXERCANT SUR DES CHARGES EXTERNES DANS LE VOISINAGE D'UN AVIONSERBIN H.1973; J. AIRCR.; U.S.A.; DA. 1973; VOL. 10; NO 2; PP. 123-124; BIBL. 4 REF.Serial Issue