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Tests Of Naca Airfoils In The Variable Density Wind Tunnel

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Tests Of N A C A Airfoils In The Variable Density Wind Tunnel

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Author : Eastman Nixon Jacobs
language : en
Publisher:
Release Date : 1936

Tests Of N A C A Airfoils In The Variable Density Wind Tunnel written by Eastman Nixon Jacobs and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1936 with Aerofoils categories.

The results of tests of six airfoils having the N.A.C.A. 230 mean line and varying in thickness from 0.06c to 0.21c are presented. These results agree with previous findings in showing that aerodynamically the best section is one of moderate thickness. The data are of value mainly in connection with the design of tapered wings having sections based on the N.A.C.A. 230 mean line.

Tests Of N A C A Airfoils In The Variable Density Wind Tunnel

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Author : Eastman Nixon Jacobs
language : en
Publisher:
Release Date : 1932

This note is the fifth of a series covering an investigation of a number of related airfoils. It presents the results obtained from tests of a group of six low-cambered airfoils in the variable density wind tunnel. The mean camber lines are identical for the six airfoils and are of such a form that the maximum mean camber is 2 percent of the chord and is a position 0.4 of the chord behnid the leading edge. The airfoils differ in thickness only, the maximum-thickness/chord ratios being ).06, 0.09, 0.12, 0.15, 0.18, and 0.21. The results have been presented in the form of both infinite and finite aspect-ratio characteristics. The values for this group of airfoils are among the highest thus far obtained, the minimum profile drags being approximately equal to those for the symmetrical series of corresponding thickness, while the maximum lift coefficients are considerably higher.