Calculation of transonic steady and oscillatory pressures on a low aspect ratio model and comparison with experimentPressure data measured by the British Royal Aircraft Establishment for the AGARD SMP tailplane are compared with results calculated using the transonic small perturbation code XTRAN3S. A brief description of the analysis is given and a recently developed finite difference grid is described. Results are presented for five steady and nine harmonically oscillating cases near zero angle of attack and for a range of subsonic and transonic Mach numbers.
Document ID
19860048489
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bennett, R. M. (NASA Langley Research Center Hampton, VA, United States)
Wynne, E. C. (NASA Langley Research Center Hampton, VA, United States)
Mabey, D. G. (Royal Aircraft Establishment Dynamics Laboratory, Bedford, United Kingdom)