A central issue in the design of aircraft is improving the lift of aircraft
wings. To assist in the design of more efficient wings, wind-tunnel tests are
performed in which the pressures at various parts of the wing are measured
generally using only a few localized pressure sensors. Recently, pressure-
sensitive paints have been developed to provide a more detailed view of wing
pressure. In these paints, a luminescent molecule is dispersed into an oxygen-
permeable paint and the aircraft wing is painted. The wing is placed into an
airfoil, and luminescence from the paint is measured. The variation in
\(\mathrm{O}_{2}\) pressure is measured by monitoring the luminescence
intensity, with lower intensity demonstrating areas of higher \(\mathrm{O}_{2}\)
pressure due to quenching.
a. The use of platinum octaethylporphyrin (PtOEP) as an oxygen sensor in
pressure-sensitive paints was described by Gouterman and coworkers [Review of
Scientific Instruments \(61(1990): 3340] .\) In this work, the following
relationship between luminescence intensity and pressure was derived:
\(I_{0} / I=A+B\left(P / P_{0}\right),\) where \(I_{0}\) is the fluorescence
intensity at ambient pressure \(P_{0},\) and \(I\) is the fluorescence intensity
at an arbitrary pressure \(P .\) Determine coefficients \(A\) and \(B\) in the
preceding expression using the Stern-Volmer equation: \(k_{\text {total}}=1 /
\tau_{l}=k_{l}+k_{q}[Q] .\) In this equation \(\tau_{l}\) is the luminescence
lifetime, \(k_{l}\) is the luminescent rate constant, and \(k_{q}\) is the
quenching rate constant. In addition, the luminescent intensity ratio is equal
to the ratio of luminescence quantum yields at ambient pressure \(\Phi_{0}\) and
an arbitrary pressure \(\Phi:\)
\\[
\Phi_{0} / \Phi=I_{0} / I
\\]
b. Using the following calibration data of the intensity ratio versus pressure
observed for PtOEP, determine \(A\) and \(B\) :
$$\begin{array}{cccc}
I_{0} / I & P / P_{0} & I_{0} / I & P / P_{0} \\
\hline 1.0 & 1.0 & 0.65 & 0.46 \\
0.9 & 0.86 & 0.61 & 0.40 \\
0.87 & 0.80 & 0.55 & 0.34 \\
0.83 & 0.75 & 0.50 & 0.28 \\
0.77 & 0.65 & 0.46 & 0.20 \\
0.70 & 0.53 & 0.35 & 0.10
\end{array}$$
c. \(A t\) an ambient pressure of 1 atm, \(I_{0}=50,000\) (arbitrary units \()\) and
40,000 at the front and back of the wing. The wind tunnel is turned on to a
speed of Mach \(0.36,\) and the measured luminescence intensity is 65,000 and
45,000 at the respective locations. What is the pressure differential between
the front and back of the wing?