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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

NUMERICAL LIFTING LIME THEORY APPLIED TO DROOPED LEADING-EDGE WINGS BELOW AND ABOVE STALLANDERSON JD JR; CORDA S; VAN WIE DM et al.1980; J. AIRCR.; ISSN 0021-8669; USA; DA. 1980; VOL. 17; NO 12; PP. 898-904; BIBL. 20 REF.Article

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A LARGE-SCALE LOW-SPEED TUNNEL TEST OF A CANARD CONFIGURATION WITH SPANWISE BLOWING.JENKINS MWM; MEYER RT.1975; IN: AM. INST. AERONAUT. ASTRONAUT AIRCR. SYST. TECHNOL. MEET.; LOS ANGELES; 1975; NEW YORK; A.I.A.A.; DA. 1975; VOL. 994; PP. 1-9; BIBL. 2 REF.Conference Paper

UNSTEADY AIRFOILSMCCROSKEY WJ.1982; ANNU. REV. FLUID MECH.; ISSN 0066-4189; USA; DA. 1982; VOL. 14; PP. 285-311; BIBL. 2 P.Article

ETUDE EXPERIMENTALE DU FLOTTEMENT D'AUBES DE COMPRESSEURSSZECHENYI E.1983; RFM, REVUE FRANCAISE DE MECANIQUE; ISSN 0373-6601; FRA; DA. 1983; NO 2; PP. 33-36; ABS. ENGArticle

TRANSONIC FLOW PAST A SYMMETRICAL AIRFOIL AT HIGH ANGLE OF ATTACKJOHNSON DA; BACHALO WD; OWEN FK et al.1981; J. AIRCR.; ISSN 0021-8669; USA; DA. 1981; VOL. 18; NO 1; PP. 7-14; BIBL. 18 REF.Article

STRAIGHT-WALLED, TWO-DIMENSIONAL DIFFUSERS-TRANSITORY STALL AND PEAK PRESSURE RECOVERYASHJAEE J; JOHNSTON JP.1980; J. FLUIDS ENG.; ISSN 0098-2202; USA; DA. 1980; VOL. 102; NO 3; PP. 275-282; BIBL. 18 REF.Article

GROWTH OF A PERTURBATION IN AN AXIAL FLOW COMPRESSORFABRI J.1979; J. ENG. POWER; ISSN 0022-0825; USA; DA. 1979; VOL. 101; NO 1; PP. 87-94; BIBL. 13 REF.Article

Progress in analysis and prediction of dynamic stallCARR, L. W.Journal of aircraft. 1988, Vol 25, Num 1, pp 6-17, issn 0021-8669Article

Evaluation of a stalled airfoil analysis programRUMSEY, C. L.Journal of aircraft. 1985, Vol 22, Num 2, pp 156-157, issn 0021-8669Article

Engineering analysis of drooped leading-edge wings near stallTAE HWAN CHO; ANDERSON, J. D. JR.Journal of aircraft. 1984, Vol 21, Num 6, pp 446-448, issn 0021-8669Article

VISUALISATION DES REGIMES INSTATIONNAIRES DES COMPRESSEURS ET DES POMPESPAULON J.1983; RFM, REVUE FRANCAISE DE MECANIQUE; ISSN 0373-6601; FRA; DA. 1983; NO 2; PP. 3-12; ABS. ENG; BIBL. 7 REF.Article

STALL FLUTTER OF LINEAR CASCADE IN COMPRESSIBLE FLOWKAJI S.1980; VIBRATIONS IN ROTATING MACHINERY. INTERNATIONAL CONFERENCE. 2/1980/CAMBRIDGE; GBR; LONDON: MECHANICAL ENGINEERING PUBLICATIONS; DA. 1980; PP. 209-214; BIBL. 5 REF.Conference Paper

Modélisation du décrochage dynamique du profil NACA 0012 = Modeling the dynamic stall of the NACA 0012 profilePETOT, D.La Recherche aérospatiale. 1984, Num 6, pp 439-442, issn 0034-1223Article

Experimental investigation of dynamic stall for a pitching airfoilDALEY, D. C; JUMPER, E. J.Journal of aircraft. 1984, Vol 21, Num 10, pp 831-832, issn 0021-8669Article

Lift-curve characteristics for an airfoil pitching at constant rateJUMPER, E. J; SCHRECK, S. J; DIMNICK, R. L et al.Journal of aircraft. 1987, Vol 24, Num 10, pp 680-687, issn 0021-8669Article

Throughflow analysis of a multistage compressor operating at near-stall conditionsDRING, R. P; JOSLYN, H. D.Journal of turbomachinery. 1987, Vol 109, Num 4, pp 483-491, issn 0889-504XArticle

Computation of the flow around wings with rear separationJACOB, K.Journal of aircraft. 1984, Vol 21, Num 2, pp 97-98, issn 0021-8669Article

Post stall studies of untwisted varying aspect ratio Slades with NACA 44 XX series airfoil sectionsOSTOWARI, C; NAIK, D.Wind engineering. 1985, Vol 9, Num 3, pp 149-164, issn 0309-524XArticle

ROTOR AIRFOILS = PROFILS AERODYNAMIQUES DES ROTORS1973; A.G.A.R.D. CONF. PROC.; FR.; DA. 1973; NO 111; PP. (72 P.); BIBL. DISSEM.; (AERODYN. ROTARY WINGS. FLUID DYN. PANEL SPEC. MEET. PAP.; MARSEILLE; 1972)Conference Paper

METHODES EXPERIMENTALES POUR L'ANALYSE DES ECOULEMENTS INSTATIONNAIRES DANS LES TURBOMACHINESLARGUIER R.1983; RFM, REVUE FRANCAISE DE MECANIQUE; ISSN 0373-6601; FRA; DA. 1983; NO 2; PP. 13-32; ABS. ENG; BIBL. 32 REF.Article

AERODYNAMIQUE SUBSONIQUE INSTATIONNAIRE D'UN PROFIL D'AILE SOUMIS A DES VARIATIONS DE VITESSE ET D'INCIDENCE = NON-STATIONARY SUBSONIC AERODYNAMICS OF A WING PROFILE SUBJECTED TO VARIATIONS OF VELOCITY AND INCIDENCEFAVIER DANIEL.1980; ; FRA; DA. 1980; PAG. MULT.; 30 CM; BIBL. 191 REF.; TH.: SCI. MATH./AIX-MARSEILLE 2/1980Thesis

AERODYNAMIC CHARACTERISTICS OF AN UNSTEADY SEPARATED FLOWFRANCIS MS; KEESEE JE; LANG JD et al.1979; A.I.A.A.J., NEW YORK; USA; DA. 1979; VOL. 17; NO 12; PP. 1332-1339; BIBL. 20 REF.Article