Effect of skewed wing-tip controls on a highly swept arrow wing at Mach number 2.03 / Emma Jean Landrum von Landrum, Emma Jean

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Wind-tunnel pressure data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from -4 ̊to 60 ̊ / Emma Jean Landrum von Landrum, Emma Jean

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Wind-tunnel force and flow visualization data at Mach numbers from 1.6 to 4.63 for a series of bodies of revolution at angles of attack from -4 ̊to 60 ̊/ Emma Jean Landrum and C. Donald Babb von Landrum, Emma Jean

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Theoretical and experimental study of twisted and cambered delta wings designed for a mach number of 3.5 / Russell B. Sorrells III, and Emma Jean Landrum ; Langley Research Center, Hampton, Va von Sorrells, Russell B

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Assessment of Analytic Methods for the Prediction of Supersonic Flow over Bodies von Landrum, Emma Jean, Miller, David S

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The Supersonic Triplet-A New Aerodynamic Panel Singularity with Directional Properties von Woodward, Frank A, Landrum, Emma Jean

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A tabulation of section aerodynamic characteristics at Mach numbers of 1.61 and 2.01 for four swept wings having the same planform but different surface shapes. Emma Jean Landrum von Landrum, Emma Jean

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Pressure distributions and aerodynamic characteristics of several spoiler controls on a 40 degree sweptback wing at a Mach number of 1.61 / by Emma Jean Landrum and K.R. Czarnecki von Landrum, Emma Jean

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Effects of a lower surface jet on the lift-drag ratio of a 45° sweptback wing at a Mach number of 2.01 / by Emma Jean Landrum : v.183 von Landrum, Emma Jean

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A tabulation of wind-tunnel pressure data and section aerodynamic characteristics at Mach numbers of 1.61 and 2.01 for two trapezoidal and three delta wings having different surface shapes / by Emma Jean Landrum von Landrum, Emma Jean

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Spanwise loadings and aerodynamic characteristics for a series of trailing-edge controls on a 40° sweptback wing at Mach numbers of 1.61 and 2.01/ Emma Jean Landrum and K. R. Czarnecki von Landrum, Emma Jean

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A tabulation of wind-tunnel pressure data and section aerodynamic characteristics at Mach numbers of 1.61 and 2.01 for a reflex cambered wing and a cambered and twisted wing having the same swept planform / by Emma Jean Landrum von Landrum, Emma Jean

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Effects at Mach numbers of 1.61 and 2.01 of camber and twist on the aerodynamic characteristics of three swept wings having the same planform / Emma Jean Landrum and K. R. Czarnecki von Landrum, Emma Jean

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Fin loads and tip-control hinge moments on a 1/8-scale model simulating the first stage of the Scout research vehicle at a mach number of 2.01 / by Ross B. Robinson and Emma Jean Landrum von Robinson, Ross B

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Application of Computer-Aided Aircraft Design in aMultidisciplinary Environment von Fulton, Robert E, Sobieszczanski, J, Storaasli, O, Landrum, Emma Jean, Loendorf, D

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A TABULATION OF SECTION AERODYNAMIC CHARACTERISTICS AT MACH NUMBERS OF 1.61 AND 2.01 FOR FOUR SWEPT WINGS HAVING THE SAME PLATFORM BUT DIFFERENT SURFACE SHAPES von LANDRUM, EMMA JEAN

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Effects at Mach Numbers of 1.61 and 2.01 of Camber and Twist on the Aerodynamic Characteristics of Three Swept Wings Having the Same Planform von Landrum, Emma Jean, Czarnecki, K. R.

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EFFECTS AT MACH NUMBERS OF 1.61 AND 2.01 OF CAMBER AND TWIST ON THE AERODYNAMIC CHARACTERISTICS OF THREE SWEPT WINGS HAFING THE SAME PLANFORM von LANDRUM,EMMA JEAN, CZARNECKI,K R

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Tabulated Data From a Pressure-Distribution Investigation at Mach Number 2.01 of a 45 Deg Sweptback-Wing Airplane Model at Combined Angles of Attack and Sideslip von Gapcynski, John P., Landrum, Emma Jean

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Compilation of Information on the Transonic Attachment of Flows at the Leading Edges of Airfoils von Lindsey, Walter F, Landrum, Emma Jean

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