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Steady inviscid transonic flows over planar airfoils: a search for a simplified procedure
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Magnus, R. Yoshihara, H. |
| Copyright Year | 1973 |
| Description | A finite difference procedure based upon a system of unsteady equations in proper conservation form with either exact or small disturbance steady terms is used to calculate the steady flows over several classes of airfoils. The airfoil condition is fulfilled on a slab whose upstream extremity is a semi-circle overlaying the airfoil leading edge circle. The limitations of the small disturbance equations are demonstrated in an extreme example of a blunt-nosed, aft-cambered airfoil. The necessity of using the equations in proper conservation form to capture the shock properly is stressed. Ability of the steady relaxation procedures to capture the shock is briefly examined. |
| File Size | 2772963 |
| Page Count | 59 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730006262 |
| Archival Resource Key | ark:/13960/t8vb2x27d |
| Language | English |
| Publisher Date | 1973-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Flow Equations Numerical Analysis Finite Difference Theory Inviscid Flow Flow Characteristics Transonic Speed Airfoils Aerodynamic Characteristics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
