This report shows that wall cooling can be an effective means of increasing the stability of laminar boundary layer flows. The stability of two general classes of cooled boundary layer flows was investigated; shock tube induced boundary layers, and cooled subsonic steady flow boundary layers (such as that on a cooled aerodynamic surface in free flight or in a wind tunnel).
Stability of highly-cooled compressible laminar boundary layers
Stabilitaet stark gekuehlter kompressibler, laminarer Grenzschichten
US Government Reports ; 1-131
1976
131 Seiten
Report
Englisch
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