Comparison of FP result with experiment

At the lowest test lift coefficient the flow is just subcritical (in the sense that the Mach number of the flow component normal to the isobars is everywhere less than unity) whilst at the other conditions shock waves of various strengths and at various locations occur. The test Reynolds number was 5.8 × 106 , based on c.
The boundary layer transition was fixed by means of small roughness elements at ξ= 0.15 on both the upper and lower wing surface. The model test conditions are slightly affected by aeroelastic model distortions (principally amounting to a variation in twist across the span) and by a spanwise variation in wall-induced upwash. Both of these effects can be expected to have some influence on the spanwise load distribution and on pressure distributions. The aeroelastic twist would tend to decrease the aerodynamic loading outboard, whilst the variation in wall-induced upwash would probably have the reverse effect.