Author: A. Warner RobinsPublisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
Characteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ration and Chord
Author: A. Warner RobinsCharacteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ratio and Chord
Author: A. Warner RobinsCharacteristics at Mach Number of 2.03 of a Series of Wings Having Various Spanwise Distributions of Thickness Ration and Chord
Author: A. Warner RobinsZero-lift Drag at Mach 1.42, 1.83, and 2.21 of a Series of Wings with Variations of Thickness Ratio and Chord
Author: Barrett L. ShroutPublisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 26
Book Description
Calculation of Aerodynamic Loading and Twist Characteristics of a Flexible Wing at Mach Numbers Approaching 1.0 and Comparison with Experiment
Author: John P.. MuglerPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 40
Book Description
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
Author: Emma Jean LandrumPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 52
Book Description
A Comparison at Mach Numbers Up to 0.92 of the Calculated and Experimental Downwash and Wake Characteristics at Various Horizonatl Tail Heights Behind a Wing with 45 Degrees of Sweepback
Author: Jack D. StephensonPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 86
Book Description
Effects of Spanwise Thickness Variation on the Aerodynamic Characteristics of 35 Degree and 45 Degree Sweptback Wings of Aspect Ratio 6
Author: William D. MorrisonPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 38
Book Description
An aerodynamic investigation has been conducted in the Langley high-speed 7- by 10-foot tunnel to determine the effects of taper-in-thickness on the aerodynamics characteristics of wings having 35 and 45 degrees of sweep-back, aspect ratio 6, and taper ratio 0.60. The wings were tapered from NACA 65A009 airfoil sections at the root chord to NACA 65A003 airfoil sections at the tip chord. The test Mach number range was from 0.60 to 1.14 at a Reynolds number of the order of 500,000.
Theoretical Pressure Distributions on Wings of Finite Span at Zero Incidence for Mach Numbers Near 1
Author: Alberta Y. AlksnePublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 58
Book Description
A method employed heretofore by the authors to obtain approximate solutions of the transonic flow equation for plane and axisymmetric flow is extended to give reasonable results for wings of finite span, consistent with the known properties of transonic flows. In this method the partial differential equation appropriate to the study of transonic flow is replaced by a nonlinear ordinary differential equation which can be solved by numerical methods. Asymptotic forms of this differential equation are given for very high and very low aspect ratios and analytic results are obtained for certain special cases. Numerical results, calculated by use of electronic computing machines, are given in the form of pressure distribution and pressure drag for two profile shapes, wedge and circular arc, for wings of rectangular plan form. The range of aspect ratios covered extends effectively from zero to infinity and agreement with the asymptotic results is shown at both limits.
Author: