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INTEGRAL EQUATION METHOD FOR SUBSONIC FLOW PAST AIRFOILS IN VENTILATED WIND TUNNELS.MOKRY M.1975; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1975; VOL. 13; NO 1; PP. 47-53; BIBL. 29 REF.Article

INSTATIONAERE DRUCKVERTEILUNGEN AN SCHWINGENDEN SCHLANKEN FLUEGEL-RUMPF-KOMBINATIONEN. VERGLEICH ZWISCHEN THEORIE UND MESSUNG. = DISTRIBUTIONS DES PRESSIONS INSTATIONNAIRES SUR LES CONFIGURATIONS AILE-FUSELAGE ELANCEES EN OSCILLATION. COMPARAISON DE LA THEORIE ET DES MESURESTRIEBSTEIN H; WAGENER J.1974; DTSCHE LUFT-U. RAUMFAHRT, FORSCH.-BER.; DTSCH.; DA. 1974; VOL. 74; NO 47; PP. 1-75; ABS. ANGL.; BIBL. 1 P. 1/2Article

USE OF SLOTTED WALLS TO REDUCE WIND-TUNNEL BOUNDARY CORRECTIONS IN SUBSONIC FLOW.PARKER AG.1974; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1974; VOL. 12; NO 2; PP. 1771-1772; BIBL. 9 REF.Article

CALCUL DES PERFORMANCES D'UNE TUYERE PROPULSIVE CONVERGENTE. COMPARAISON AVEC L'EXPERIENCE.FENAIN M; DUTOUQUET L; SOLIGNAC JL et al.1974; INT: 9TH CONGR. INT. COUNC. AERONAUT. SCI. PROC.; HAIFA; 1974; JERUSALEM; WEIZMANN SCI. PRESS ISR.; DA. 1974; VOL. 2; PP. 691-705; BIBL. 7 REF.Conference Paper

FLOW SEPARATION OVER AXISYMMETRIC AFTERBODY MODELS.PRESZ WM JR; PITKIN ET.1974; J. AIRCR.; U.S.A.; DA. 1974; VOL. 11; NO 11; PP. 677-682; BIBL. 15 REF.Article

LA VEINE D'ESSAIS DE LA SOUFFLERIE SUBSONIQUE DE TOULOUSE (FRANCE).LAFITTE J.1976; ACIER STAHL STEEL; FR.; DA. 1976; VOL. 41; NO 4; PP. 141-145Article

SPHERE DRAG COEFFICIENT FOR SUBSONIC SPEEDS IN CONTINUUM AND FREE-MOLECULE FLOWS.BAILEY AB.1974; J. FLUID MECH.; G.B.; DA. 1974; VOL. 65; NO 2; PP. 401-410; BIBL. 24 REF.Article

A TWO-DIMENSIONAL AEROFOIL WITH A CONTROL SURFACE OSCILLATING AT LOW FREQUENCY IN HIGH SUBSONIC FLOW.NIXON D.1974; AERONAUT. QUART.; G.B.; DA. 1974; VOL. 25; NO 3; PP. 186-198; BIBL. 4 REF.Article

NUMERICAL SIMULATION OF THE WIND TUNNEL ENVIRONMENT BY A PANEL METHODLEE KD.1980; AERODYNAMICS TESTING CONFERENCE. 11/1980/COLORADO SPRINGS CO; USA; NEW YORK: AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS; DA. 1980; PP. 24-30; BIBL. 13 REF.Conference Paper

THE CALCULATION OF SUBSONIC AND TRANSONIC TURBULENT BOUNDARY LAYERS ON AN INFINITE YAWED AIRFOIL.ADAMS JC JR.1974; IN: AM. INST. AERONAUT. ASTRONAUT. 7TH FLUID PLASMA DYN. CONF.; PALO ALTO, CALIF.; 1974; NEW YORK; A.I.A.A.; DA. 1974; VOL. 557; PP. 1-18; BIBL. 2 P.Conference Paper

PENETRATION D'UN CONE DANS UN FLUIDE COMPRESSIBLEPORUCHIKOV VB.1973; PRIKL. MAT. MEKH.; S.S.S.R.; DA. 1973; VOL. 37; NO 1; PP. 84-93; BIBL. 8 REF.Serial Issue

A SUBSONIC DIFFUSER WITH MOVING WALLS FOR BOUNDARY-LAYER CONTROLTENNANT JS.1973; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1973; VOL. 11; NO 2; PP. 240-242; BIBL. 9 REF.Serial Issue

BLOCAGE SUBSONIQUE DANS UNE TUYERE A DEUX FLUXMARCHAL R; PAGE E; SERVANTY P et al.1981; C.R. SEANCES ACAD. SCI., SER. 2; ISSN 0567-6541; FRA; DA. 1981; VOL. 292; NO 18; PP. 1241-1242; ABS. ENG; BIBL. 1 REF.Article

HEAT TRANSFER EFFECTS ON A DELTA WING IN SUBSONIC FLOW. = EFFETS DU TRANSFERT DE CHALEUR SUR UNE AILE EN DELTA EN ECOULEMENT SUBSONIQUEBLOHM RW III; MARCHMAN JF III.1974; IN: HEAT TRANSFER FLUID MECH. INST. 24TH MEET. PROC.; CORVALLIS, OREG.; 1974; STANFORD, CALIF.; STANFORD UNIV.; DA. 1974; PP. 220-235; BIBL. 5 REF.Conference Paper

CORPS MINCE DANS UN ECOULEMENT GAZEUX SUBSONIQUE LIMITEKHOLYAVKO VI.1974; IZVEST. AKAD. NAUK S.S.S.R., MEKH. ZHIDKOSTI GAZA; S.S.S.R.; DA. 1974; NO 3; PP. 173-176Article

SUBSONIC AERODYNAMICSDELAURIER JD; REID LD.1978; INST. AEROSPACE STUD., UNIV. TORONTO, ANNU. PROGR. REP.; CAN; DA. 1978; PP. 57-58; BIBL. 7 REF.Article

HYDROGEN FOR THE SUBSONIC TRANSPORT.KORYCINSKI PF; SNOW DB.1975; IN: HYDROGEN ENERGY. HYDROGEN ECON. ENERGY CONF.; MIAMI BEACH, FLA.; 1974; NEW YORK; PLENUM PRESS; DA. 1975; PP. 819-838; BIBL. 12 REF.Conference Paper

IL-22 : A critical mediator in mucosal host defenseAUJLA, S. J; KOLLS, J. K.Journal of molecular medicine (Berlin. Print). 2009, Vol 87, Num 5, pp 451-454, issn 0946-2716, 4 p.Article

ETUDE DES ECOULEMENTS MIXTES TRIDIMENSIONNELS DANS LES TUYERES AVEC ENTREE ASYMETRIQUEDVORETSKIJ VM.1975; IZVEST. AKAD. NAUK S.S.S.R., MEKH. ZHIDKOSTI GAZA; S.S.S.R.; DA. 1975; NO 2; PP. 167-169; BIBL. 9 REF.Article

SUBSONIC FLOW INTO A DOWNSTREAM FACING INLET.KEITH TG JR.1974; J. AIRCR.; U.S.A.; DA. 1974; VOL. 11; NO 4; PP. 251-252; BIBL. 1 REF.Article

METHODE DE CALCUL DES DERIVEES AERODYNAMIQUES LONGITUDINALES, LATERALES ET CROISEES D'UN APPAREIL VOLANT AUX VITESSES SUBSONIQUESGANIEV FI.1978; IZVEST. AKAD. NAUK S.S.S.R., MEKH. ZHIDKOSTI GAZA; S.S.S.R.; DA. 1978; NO 2; PP. 77-88; BIBL. 12 REF.Article

OSCILLATIONS OF A WEDGE IN A FREE STREAM WITH PARTICULAR REFERENCE TO PARACHUTES.REDDY KR; ROBERTS BW.1975; APPL. SCI. RES.; NETHERL.; DA. 1975; VOL. 31; NO 4; PP. 279-308Article

THREE YEARS OF OPERATION OF THE ONERA PRESSURIZED SUBSONIC WIND TUNNELCARRARA JM; MASSON A.sdICAS 1980. INTERNATIONAL COUNCIL OF THE AERONAUTICAL SCIENCES. CONGRESS. 12/1980/MUNICH; USA; DA. S.D.; PP. 778-792; BIBL. 5 REF.Conference Paper

Welche Kältemittel in der Zukunft? = Which refrigerant in the future?DOÊRING, R.Die Kälte und Klimatechnik. 1990, Vol 43, Num 9, pp 472-482, issn 0343-2246, 6 p.Article

SUPPRESSION DES AUTO-OSCILLATIONS DANS LES SOUFFLERIES A PARTIE ACTIVE OUVERTEBOYARCHIKOVA M YU; VLASOV EV; GINEVSKIJ AS et al.1982; IZV. AKAD. NAUK SSSR, MEH. ZIDK. GAZA; ISSN 0568-5281; SUN; DA. 1982; NO 1; PP. 126-132; BIBL. 4 REF.Article

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