Download Free The Effect Of Camber And Twist On Wing Pressure Distributions For Mach Numbers From 2 To 76 Book in PDF and EPUB Free Download. You can read online The Effect Of Camber And Twist On Wing Pressure Distributions For Mach Numbers From 2 To 76 and write the review.

An investigation has been conducted in the MIT Aerophysics Laboratory wind tunnel to determine the effects of body camber on the pressure distribution over a cone-cylinder type body and on the forces on wings attached to the body. Three models were tested, one being a straight cone-cylinder and the other two, similar in cross-ection, having cambered axes. Tabulated data from these tests were presented in an earlier report. The present report attempts to analyze some of the data from a theoretical viewpoint. The effect of body camber is considered as a disturbance to the flow field about a straight body. Slender body theory in a slightly modified form is used to predict the effect of this disturbance on the pressure re-distribution for the body and on the forces on the attached wing surfaces. In applying this method, the pressures and wing forces for the straight body are assumed known exactly (from experiment in the present comparisons). The prediction is reasonably successful in most of the examples analyzed.
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.