F16 – Lecture Notes: Shock Losses and Compressible-Flow Pitot Tube

F16 – Lecture Notes 1. Shock Losses 2. Compressible-Flow Pitot Tube Reading: Anderson 8.6, 8.7 Shock Losses Stagnation pressure jump relation The stagnation pressure ratio across the shock is p2 p o2 = p o1 p1 ⎦ 1+ 1+ ��/(�−1) �−1 M22 2 �−1 M12 2 (1) where both p2 /p1 and M2 are functions of the upstream Mach number M1 , as derived previ­ ously. The figures show the po2 /po1 ratio, with the second figure showing an expanded scale near M1 � 1. 1.0 0.9 0.8 po2/po1 0.7 0.6 0.5 0.4 0.3 0.2 0.1 0.0 1.0 1.2 1.4 1.6 1.8 2.0 M1 2.2 2.4 2.6 2.8 3.0 1.15 1.2 1.25 M1 1.3 1.35 1.4 1.45 1.5 1.00 0.99 0.98 po2/po1 0.97 0.96 0.95 0.94 0.93 1.0 1.05 1.1 The fractional shock total-pressure loss 1 − po2 /po1 is seen to be small for M1 close to unity, but increases rapidly for higher Mach numbers. Minimizing this loss is of great practical importance, since it cuts directly into the performance of supersonic air-breathing engines. 1 Compressible-Flow Pitot Tube Subsonic pitot tube A pitot tube in subsonic flow measures the local total pressure po . Together with a mea­ surement of the static pressure p, the Mach number can be computed from the po /p ratio relation. po = p M2 M, p ⎣ � −1 2 1+ M 2 �⎦ 2 � po = � −1 p ⎤�/(�−1) �(�−1)/� � − 1⎡ (2) po po p p s p po p po The pitot-static combination therefore constitutes a Mach meter . With M 2 known, we can then also determine the dynamic pressure. �⎦ 1 � po � �V 2 = pM 2 = p� 2 2 � −1 p �(�−1)/� � − 1⎡ (3) The velocity can be determined from V 2 = a2 M 2 = a2o M 2 1 + �−1 M2 2 but this requires knowing either the static speed of sound a, or the stagnation speed of sound ao . The latter can be obtained by measuring the stagnation temperature at the tip of the pitot probe. Supersonic pitot tube A pitot probe in a supersonic stream will have a bow shock ahead of it. This complicates the flow measurement, since the bow shock will cause a drop in the total pressure, from po1 to po2 , the latter being sensed by the pitot port. It’s useful to note that the shock will also cause a drop in �o , but ho will not change. The pressures and Mach number immediately behind the shock are related by p o2 = p2 ⎣ � −1 2 1+ M2 2 2 ⎤�/(�−1) ho1 ho2 h2 h1 �o1 2 �2 �1 M1 , p1 �o po1 po2 p2 p1 bow shock po2 po2 In addition, we also have M2 and p2 /p1 as functions of M1 from the earlier normal-shock analysis. Combining these produces the relation between the po2 measured by the pitot probe, the static p1 , and the required flow Mach number M1 . After some manipulation, the result is the Rayleigh Pitot tube formula. po p2 p o2 = 2 = p1 p2 p1 ⎦ (� +1)2 M12 4�M12 − 2(� −1) ��/(�−1) 1 − � + 2�M12 � +1 (4) The figure shows po2 /p1 versus M1 , compared with the isentropic ratio po1 /p1 . p o1 = p1 ⎣ 1 + � −1 2 M1 2 ⎤�/(�−1)� (5)� Only the latter is plotted for M1 < 1, where there is no bow shock, and so equation (4) does not apply. The effect of the pitot bow shock’s total pressure loss, indicated by the difference po1 − po2 , becomes substantial at larger Mach numbers. Ideally, we would like to have the pitot formula (4) give M1 as an explicit function of the pitot/static pressure ratio po2 /p1 . However, this is not possible due to its complexity, so a numerical solution is required. The function is also readily available in table form. 3 6.0 5.5 5.0 po1/p1 4.5 po2/p1 4.0 3.5 3.0 2.5 2.0 1.5 1.0 0.0 0.2 0.4 0.6 0.8 1.0 M1 1.2 4 1.4 1.6 1.8 2.0