1 edition of Comparison of the full-potential and Euler formulations for computing transonic airfoil flows found in the catalog.
Published 1984 by Administrator in National Aeronautics and Space Administration, Ames Research Center
June 1984--Cover.N84-31094--Microfiche header.Includes bibliographical references.Microfiche. [Washington, D.C.? : National Aeronautics and Space Administration, 1984]. 1 microfiche ; 11 x 15 cm.
|Statement||National Aeronautics and Space Administration, Ames Research Center|
|Publishers||National Aeronautics and Space Administration, Ames Research Center|
|The Physical Object|
|Pagination||xvi, 129 p. :|
|Number of Pages||90|
|2||NASA technical memorandum -- 85983.|
nodata File Size: 6MB.
89 was used for the Boeing 747 results in Figure 7-12.Aerodynamics for Naval Aviators, Revised edition, 1965, published by Direction of the Commander, Naval Air Systems Command, United States Navy, reprinted by Aviation Supplies and Academics, Inc. In the algorithm, an improved NND Non-oscillatory, Non-free--parameter, Dissipative scheme which is a kind of the TVD Total Variation Diminishing schemes is adopted.
As the freestream Mach number increases further, a region of supersonic flow develops. Attached Flow Maneuver Wing Design: To push performance past the cruise lift condition the situation changes.
24 Sergio Iglesias and W. The calculated instantaneous pressure coefficient distribution during a cycle of motion compare well with the related numerical and experimental data. Although it is possible to design an airfoil to have a shock-free recompression, this situation is usually possible for only a single combination of Mach number and lift coefficient.
The manuscript ponders on the design and numerical analysis of vortex methods, shock calculations and the numerical solution of singular perturbation problems, tracking of interfaces for fluid flow, and transonic flows with viscous effects. In the days of propeller airplanes the transonic flow limitations on the propeller mostly kept airplanes from flying fast enough to encounter transonic flow over the rest of the airplane. The selection first elaborates on computational fluid dynamics of airfoils and wings; shock-free configurations in two- and three-dimensional transonic flow; and steady-state solution of the Euler equations for transonic flow.
In the algorithm, an improved NND Non-oscillatory, Non-free--parameter, Dissipative scheme which is a kind of the TVD Total Variation Diminishing schemes is adopted.
Here the propeller was moving much faster than the airplane, and adverse transonic aerodynamic problems appeared on the prop first, limiting the speed and thus transonic flow problems over the rest of the aircraft.
This typical progression of the flow pattern, as shown in Figure 1-1, leads to rapid variations in drag, lift and pitching moment with change in Mach number.