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Results 1 to 25 of 770

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CASCADE WITH SUBSONIC LEADING-EDGE LOCUS.GOLDSTEIN ME.1975; A.I.A.A. J., NEW YORK; U.S.A.; DA. 1975; VOL. 13; NO 8; PP. 1117-1119; BIBL. 3 REF.Article

STUDIES OF LEADING-EDGE THUST PHENOMENACARLSON HW; MACK RJ.1980; J. AIRCR.; ISSN 0021-8669; USA; DA. 1980; VOL. 17; NO 12; PP. 890-897; BIBL. 14 REF.Article

AUGMENTATION OF VORTEX LIFT BY SPANWISE BLOWING.CAMPBELL JF.1975; IN: AM. INST. AERONAUT. ASTRONAUT AIRCR. SYST. TECHNOL. MEET.; LOS ANGELES; 1975; NEW YORK; A.I.A.A.; DA. 1975; VOL. 993; PP. 1-6; H.T. 3; BIBL. 19 REF.Conference Paper

TRANSONIC EQUIVALENCE RULE: A NONLINEAR PROBLEM INVOLVING LIFT.CHENG HK; HAFEZ MM.1975; J. FLUID MECH.; G.B.; DA. 1975; VOL. 72; NO 1; PP. 161-187; BIBL. 1 P. 1/2Article

TRAGENDE SCHNABELPROFILE IN STOSSFREIER SCHALLANSTROEMUNG. = PROFILS PORTANTS A BORDS D'ATTAQUE AIGUS DANS UN ECOULEMENT INCIDENT TRANSSONIQUE SANS CHOCSOBIECZKY H.1975; Z. ANGEW. MATH. PHYS.; SCHWEIZ; DA. 1975; VOL. 26; NO 6; PP. 819-830; ABS. ANGL.; BIBL. 4 REF.Article

FREE CONVECTION HEAT TRANSFER NEAR LEADING EDGE OF SEMI-INFINITE VERTICAL FLAT PLATE WITH FINITE THICKNESS (1ST. REPORT, ISOTHERMAL FLAT PLATE, PR=0.72)MIYAMOTO M; AKIYOSHI T.1981; BULL. JSME; ISSN 0021-3764; JPN; DA. 1981; VOL. 24; NO 197; PP. 1945-1952; BIBL. 15 REF.Article

DESIGN OF FLAT PLATE LEADING EDYES TO AVOID FLOW SEPARATIONDAVIS MR.1980; AIAA J.; ISSN 0001-1452; USA; DA. 1980; VOL. 18; NO 5; PP. 598-600; BIBL. 9 REF.Article

THE EFFECTS OF LEADING EDGE MODIFICATIONS ON THE POST-STALL CHARACTERISTICS OF WINGSWINKELMANN AE; BARLOW JB; SAINI JK et al.1980; AEROSPACE SCIENCES MEETING. 18/1980/PASADENA CA; USA; NEW YORK: AIAA; DA. 1980; 15 P.; BIBL. 18 REF.Conference Paper

A TRANSONIC PROPELLER OF TRIANGULAR PLAN FORM (AN EXTENSION)RIBNER HS.1978; U.T.I.A.S. TECH. NOTE; CAN; DA. 1978; NO 218; PP. 1-17; BIBL. 6 REF.; 7 ILL.Serial Issue

INVISCID ANALYSIS OF TRANSONIC, SLATTEDAIRFOILS.CAUGHEY DA.1976; J. AIRCR.; U.S.A.; DA. 1976; VOL. 13; NO 1; PP. 29-35; BIBL. 14 REF.Article

SICHTBARMACHUNG DER UMSTROEMUNG ZWEIER RAUMGLEITERKONFIGURATIONEN IM UNTERSCHALLBEREICH. = VISUALISATION DE L'ECOULEMENT AUTOUR DE DEUX PROFILS DANS LE DOMAINE SUBSONIQUEBIPPES H; COLAK ANTIC P.1975; DTSCHE LUFT- U. RAUMFAHRT, FORSCH.-BER.; DTSCH.; DA. 1975; VOL. 75; NO 49; PP. 1-45; H.T. 14; ABS. ANGL.; BIBL. 2 P.Serial Issue

SUPERCAVITATING LINEAR CASCADES WITH ROUNDED NOSES.FURUYA O.1974; J. FLUIDS ENGNG; U.S.A.; DA. 1974; VOL. 96; NO 1; PP. 35-42; BIBL. 13 REF.Article

LEADING-EDGE FORCE FEATURES OF THE AERODYNAMIC FINITE ELEMENT METHOD = CARACTERISTIQUES DES FORCES AU BORD D'ATTAQUE DANS LA METHODE AERODYNAMIQUE PAR ELEMENTS FINISCHUAN TAU LAN; ROSKAM J.1972; J. AIRCR.; U.S.A.; DA. 1972; VOL. 9; NO 12; PP. 864-867; BIBL. 13 REF.Serial Issue

VORTEX-LATTICE METHOD FOR THE CALCULATION OF THE NONSTEADY SEPARATED FLOW OVER DELTA WINGSLEVIN D; KATZ J.1981; J. AIRCR.; ISSN 0021-8669; USA; DA. 1981; VOL. 18; NO 12; PP. 1032-1037; BIBL. 21 REF.Article

ON LIFT OF DELTA WINGS WITH LEADING-EDGE VORTICESHAYASHIDA M; SATO M; MATSUOKA K et al.1977; BULL. UNIV. OSAKA PREFECT., A; JPN; DA. 1977; VOL. 26; NO 2; PP. 37-51; BIBL. 19 REF.Article

UNSTEADY AERODYNAMICS OF SLENDER DELTA WINGS AT LARGE ANGLES OF ATTACK.ERICSSON LE; REDING JP.1975; J. AIRCR.; U.S.A.; DA. 1975; VOL. 12; NO 9; PP. 721-729; BIBL. 41 REF.Article

A SOLUTION FOR CONICALLY CAMBERED DELTA WINGS IN SUPERSONIC FLOW.MATEESCU D.1975; REV. ROUMAINE SCI. TECH., MEC. APPL.; ROUMAN.; DA. 1975; VOL. 20; NO 2; PP. 189-216; BIBL. 7 REF.Article

METHODE PARAMETRIQUE DE RESOLUTION GENERALE DES PROBLEMES DE COUCHE LIMITE LAMINAIRELOJTSYANSKIJ LG.1974; IN: IZBR. PROBL. PRIKL. MEKH.; MOSKVA; VINITI; DA. 1974; PP. 467-474; BIBL. 11 REF.Book Chapter

SINGULARITY AT THE TRAILING EDGE OF A SWEPT WINGCLAPWORTHY GJ.1979; A.I.A.A. J., NEW YORK; USA; DA. 1979; VOL. 17; NO 3; PP. 313-315; BIBL. 5 REF.Article

CARACTERISTIQUES DE TREMBLEMENT DE DEUX TYPES DE PROFILS SUBSONIQUES.TENSI J; LI FANG TSEN.1975; C.R. ACAD. SCI., B; FR.; DA. 1975; VOL. 281; NO 11; PP. 149-152; ABS. ANGL.; BIBL. 7 REF.Article

ETUDE NUMERIQUE DU BORD D'ATTAQUE, BASEE SUR L'EQUATION COMPLETE DE BOLTZMANNSHCHERBAK S YA.1974; VEST. LENINGRAD. UNIV.; S.S.S.R.; DA. 1974; NO 19; PP. 109-115; ABS. ANGL.; 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

STUDIES OF LEADING-EDGE THRUST PHENOMENACARLSON HW; MACK RJ.1980; AEROSPACE SCIENCES MEETING. 18/1980/PASADENA CA; USA; NEW YORK: AIAA; DA. 1980; 10 P.; BIBL. 14 REF.Conference Paper

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

CALCULATED LEADING-EDGE BLUNTNESS EFFECT ON TRANSONIC COMPRESSOR NOISE.FINK MR.1975; J. AIRCR.; U.S.A.; DA. 1975; VOL. 12; NO 8; PP. 631-632; BIBL. 7 REF.Article

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