Effects of Mach Number Up to 0.34 and Reynolds Number Up to 8,000,000 on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections PDF Download

Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Effects of Mach Number Up to 0.34 and Reynolds Number Up to 8,000,000 on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections PDF full book. Access full book title Effects of Mach Number Up to 0.34 and Reynolds Number Up to 8,000,000 on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections by G. Chester Furlong. Download full books in PDF and EPUB format.

Effects of Mach Number Up to 0.34 and Reynolds Number Up to 8,000,000 on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections

Effects of Mach Number Up to 0.34 and Reynolds Number Up to 8,000,000 on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections PDF Author: G. Chester Furlong
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 52

Book Description
The effects of Mach numbers up to 0.34 and Reynolds number up to 8,000,000 on the maximum lift coefficient of the wing of NACA 66-weries airfoil sections are presented. The wing was tested with full-span and partial-span split flaps deflected 60 degrees and without flaps. The results indicated that the peak values of maximum lift coefficient occurred at free-stream Mach numbers of approximately 0.212 and 0.227 for the flaps-retracted configuration and 0.138 and 0.196 for the full-span flaps-deflected configuration for tunnel pressures of 33 and 14.7 pounds per square inch, respectively.
➤