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Experimental and Theoretical Aerodynamic Characteristics of Two Low-aspect-ratio Delta Wings at Angles of Attack to 50 Degrees at a Mach Number of 4.07
FRED M. SMITH
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Abstract
Report presenting an investigation conducted in the 9- by 9-inch Mach number 4 blowdown jet to determine the aerodynamic characteristics of two double-wedge-section delta wings of aspect ratio 1.3 and 2.3 to angles of attack of 50 degrees at a Mach number of 4.07. The results are compared with the predictions of linear theory, two-dimensional shock-expansion theory, Newtonian-impact theory, and a method which utilizes the shock-wave and expansion-wave equations expanded by the two-dimensional hypersonic-flow similarity parameter.