A study was conducted in the NASA Glenn Research Center (NASA-GRC) linear cascade on the intermittent flow on the suction surface of an airfoil section from the tip region of a modern low aspect ratio fan blade. Experimental results revealed that. at a large incidence angle. a range of transonic inlet Mach numbers exist where the leading-edge shock-wave pattern was unstable. https://danddcollectiblers.shop/product-category/luncheon-napkins/