Low-speed Experimental Investigation of a Thin, Faired, Double-wedge Airfoil Section with Nose and Trailing-edge Flaps PDF Download
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Author: Leonard M. Rose Publisher: ISBN: Category : Aerofoils Languages : en Pages : 28
Book Description
A faired, double-wedge airfoil section, 4.23 percent thick, was investigated with plain nose and trailing-edge flaps. The nose flap was 0.16 chord of the airfoil and the trailing-edge flap was 0.25 chord of the airfoil. Section lift, drag, and pitching-momnet data are presented for a Reynolds number of 5,800,000 which corresponded to a Mach number of 0.17.
Author: Leonard M. Rose Publisher: ISBN: Category : Aerofoils Languages : en Pages : 28
Book Description
A faired, double-wedge airfoil section, 4.23 percent thick, was investigated with plain nose and trailing-edge flaps. The nose flap was 0.16 chord of the airfoil and the trailing-edge flap was 0.25 chord of the airfoil. Section lift, drag, and pitching-momnet data are presented for a Reynolds number of 5,800,000 which corresponded to a Mach number of 0.17.
Author: P. W. Kuhns Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 736
Book Description
Equations are derived to evaluate the effects of thermal vibration relaxation and specific-heat changes on pneumatic-probe pyrometer measurements in the region 1000 to 3000 degrees K and 0.3
Author: John D. Stanitz Publisher: ISBN: Category : Aeronautics Languages : en Pages : 712
Book Description
Six numerical examples are presented for steady, two-dimensional, compressible, nonviscous flow in centrifugal compressors with straight blades. A seventh example is presented for incompressible flow. The solutions also applye to radial-flow turbines with rotation and flow direction reversed. The effects of variations in following parameters were investigated: (1) flow rate, (2) impeller-tip speed, (3) variation of passage height with radius, and (4) number of blades. The numerical results are presented in plots of the streamlines, constant Mach number lines, and constant pressure-ratio lines. Correlation equations are developed whereby the flow conditions in any impeller with straight blades can be determined for all operating conditions.
Author: Leonard M. Rose
Author: Leonard M. Rose
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: P. W. Kuhns
Author: 
Author: 
Author: John D. Stanitz
Author: