Semispan wing models were tested in Langley supersonic tunnel at Re from 1.9×106 to 6.5×106 based on mean geometric chord; complex wing forms with thickened roots, extended root chords, and higher volumes show lower zero lift wave drags than plain swept wings.
Characteristics at mach number of 2.03 of series of wings having various spanwise distributions of thickness ratio and chord
NASA -- Tech Note
1960
26 pages
Report
English
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Relation between spanwise variations in critical Mach number and spanwise load distributions
Engineering Index Backfile | 1944
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