[
{
"id": "authors:6c106-ame27",
"collection": "authors",
"collection_id": "6c106-ame27",
"cite_using_url": "https://resolver.caltech.edu/CaltechAUTHORS:20140805-133252590",
"type": "monograph",
"title": "Two-dimensional irrotational mixed subsonic and supersonic flow of a compressible fluid and the upper critical Mach number",
"author": [
{
"family_name": "Tsien",
"given_name": "Hsue-Shen",
"clpid": "Tsien-H-S"
},
{
"family_name": "Kuo",
"given_name": "Yung-Huai",
"clpid": "Kuo-Y-H"
}
],
"abstract": "The problem of flow of a compressible fluid past a body with subsonic flow at infinite is formulated by the hodograph method. The solution in the hodograph plane is first constructed about the origin by superposition of the particular integrals of the transformed equations of motion with a set of constants which would determine, in the limiting case, a known incompressible flow. This solution is then extended outside the circle of convergence by analytic continuation.",
"publisher": "National Advisory Committee on Aeronautics",
"publication_date": "1945-05"
},
{
"id": "authors:htc09-znt63",
"collection": "authors",
"collection_id": "htc09-znt63",
"cite_using_url": "https://resolver.caltech.edu/CaltechAUTHORS:20140805-134608325",
"type": "monograph",
"title": "The \"limiting line\" in mixed subsonic and supersonic flow of compressible fluids",
"author": [
{
"family_name": "Tsien",
"given_name": "Hsue-Shen",
"clpid": "Tsien-H-S"
}
],
"abstract": "It is well known that the vorticity for any fluid element is constant if the fluid is non-viscous and the change of state of the fluid is isentropic. When a solid body is placed in a uniform stream, the flow far ahead of the body is irrotational. Then if the flow is further assumed to be isentropic, the vorticity will be zero over the whole field of flow. In other words, the flow is irrotational. For such flow over a solid body, it is shown by Theodorsen that the solid body experiences no resistance. If the fluid has a small viscosity, its effect will be limited in the boundary layer over the solid body and the body will have a drag due to the skin friction. This type of essentially isentropic irrotational flow is generally observed for a streamlined body placed in a uniform stream, if the velocity of the stream is kept below the so-called \"critical speed.\" At the critical speed or rather at a certain value of the ratio of the velocity of the undisturbed flow and the corresponding velocity of sound, shock waves appear. This phenomenon is called the \"compressibility bubble.\" Along a shock wave, the change of state of the fluid is no longer isentropic, although still adiabatic. This results in an increase in entropy of the fluid and generally introduces vorticity in an originally irrotational flow. The increase in entropy of the fluid is, of course, the consequence of changing part of the mechanical energy into heat energy. In other words, the part of fluid affected by the shock wave has a reduced mechanical energy. Therefore, with the appearance of shock waves, the wake of the streamline body is very much widened, and the drag increases drastically. Furthermore, the accompanying change in the pressure distribution over the body changes the aerodynamic moment acting on it and in the case of an airfoil decreases the lift force. All these consequences of the breakdown of isentropic irrotational flow are generally undesirable in applied aerodynamics. Its occurrence should be delayed as much as possible by modifying the shape or contour of the body. However, such endeavor will be very much facilitated if the cause or the criterion for the breakdown can be found first.",
"publisher": "National Advisory Committee on Aeronautics",
"publication_date": "1944-11"
}
]