Low-speed Experimental Investigation of a Thin, Faired, Double-wedge Airfoil Section with Nose and Trailing-edge Flaps

Low-speed Experimental Investigation of a Thin, Faired, Double-wedge Airfoil Section with Nose and Trailing-edge Flaps
Author: Leonard M. Rose
Publisher:
Total Pages: 28
Release: 1949
Genre: Aerofoils
ISBN:

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.

Report

Report
Author:
Publisher:
Total Pages: 620
Release: 1945
Genre: Aeronautics
ISBN:

Two-dimensional Compressible Flow in Centrifugal Compressors with Straight Blades

Two-dimensional Compressible Flow in Centrifugal Compressors with Straight Blades
Author: John D. Stanitz
Publisher:
Total Pages: 712
Release: 1949
Genre: Aeronautics
ISBN:

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.