Abstract:

ESDU 93026 illustrates by case studies the use of the information in Parts 1 and 2 on the use of vortex generators to control shock-induced separation. The examples are the control of internal noise by the application of vortex generators on the forward cabin roof of a business aircraft (Gulfstream III), the control of separation associated with a three-shock pattern near the tip of a highly swept and tapered model wing in a wind-tunnel, and the improvement of the buffet manoeuvre boundary on a straight wing interceptor aircraft of the fifties (Avro Canada CF-100). In each case the geometric details of the arrays of vortex generators tested are provided, the results obtained are described, and the aerodynamic principles involved that influence those results are assessed.