An experimental study of supersonic wing tip vortices has been conduct
ed at Mach 2.49 using small-scale four-hole and five-hole conical prob
es, The study was performed 2.25 chords downstream of a semispan recta
ngular wing at angles of attack of 5.7 and 10.4 deg. The main objectiv
e of the experiments was to determine the Mach number, flow angularity
and total pressure distribution in the core region of supersonic wing
tip vortices. A secondary aim was to demonstrate the feasibility of c
alibrating a conical probe using a computational solution to predict t
he flow characteristics. Results of the present investigation showed t
hat the numerically generated calibration data can be used for pointed
nose four-hole conical probes but were not sufficiently accurate for
conventional five-hole probes due to nose bluntness effects. A combina
tion of four-hole conical probe measurements with independent pitot pr
essure measurements indicated a significant Mach number and total pres
sure deficit in the core regions of supersonic wing tip vortices, comb
ined with an asymmetric ''Burger-like'' swirl distribution.