What do your results mean?
This guide explains the POSTPRO generated by the TS Aero App. T If you still have questions regarding your results, please email us at firstname.lastname@example.org
Plots and Movie Slices
This chart will list variables that could be generated by your App. Solutions usually include but are not limited to the following
The coefficients are normalized by freestream dynamic pressure. Dynamic pressure is equal to the one half of the fluid density and freestream velocity.
Cf and tauwMean also include LIC images and slices. LIC is surface streamlines overlaid on the surface to indicate the vector orientation of the local shear-stress.
TS Aero VTOL tool users may see pGauage, pTot, pX, pY, and pZ. The variables are normalized by the freestream velocity if the input is greater than 1 m/s.
Pictured above are sample results from the AIAA 3rd High Lift Prediction Workshop. From the CL vs AOA curve, we saw the CL dropped off at 20.59 deg. The drop-off signals that the aircraft performance has stalled. However, if you look at the Skin-Friction plot above, you can see local sections of the wing have begun to stall at 18.58 deg.
From the CpY above, we can see a positive CpY on the right side of the vehicle and a negative CpY on the left side. In this case the aircraft is oriented such that the Y axis points out the right side of the aircraft. Hence as the flow accelerates off the front cabin, the low pressure wants to suck the right-hand-side of the aircraft out to the right (+Y direction) and the left-hand-side to the left (-Y direction). For symmetric steady state runs, the magnitudes are similar and thus summing the right and left sides of the aircraft tends to equate to a near zero value
In the the CpZ plots above, the forces are summed in the z-direction. Low CpZ equates to regions of downforce while high CpZ equates to regions of lift. The plots above show large regions of lift along the top surface of the wing while downforce along the bottom of the wing. Pressure on the top surface of the wing is greater than the pressure on the bottom surface, therefore, generating lift for the aircraft to fly.
TS Aero generates span plots as a POSTPRO item for your run. Cf Force X, Cf Force Z, Cp Force X, Cp Force Z, Sum X, and Sum Z are the generated plots. The area under the curve divided by the reference area is equal to the coefficient in that direction. For Sum X and Sum Z, it would equal to the Drag Coefficient and Lift Coefficient respectively.