Pressure Distribution Over a Rectangular Monoplane Wing Model up to 90 Degree Angle of Attack
This is a 1929 NASA technical report, issued as a government aeronautics research document, that presents measured pressure distribution data for a rectangular monoplane wing model tested across angles of attack up to 90 degrees. Its pages are engineering line plots of pressure against chord position for each angle, arranged as stacked three-dimensional graphs with figure labels and key legends. A designer could take from them the layered, receding perspective of stacked curves and the stepped rhythm of repeated profiles, useful for abstract line-based patterns.
