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Boundary-layer transition and displacement thickness effects on zero-lift drag of a series of power-law bodies at mach 6
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Ashby Jr., G. C. Harris, J. E. |
| Copyright Year | 1974 |
| Description | Wave and skin-friction drag have been numerically calculated for a series of power-law bodies at a Mach number of 6 and Reynolds numbers, based on body length, from 1.5 million to 9.5 million. Pressure distributions were computed on the nose by the inverse method and on the body by the method of characteristics. These pressure distributions and the measured locations of boundary-layer transition were used in a nonsimilar-boundary-layer program to determine viscous effects. A coupled iterative approach between the boundary-layer and pressure-distribution programs was used to account for boundary-layer displacement-thickness effects. The calculated-drag coefficients compared well with previously obtained experimental data. |
| File Size | 1279339 |
| Page Count | 66 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740024638 |
| Archival Resource Key | ark:/13960/t4mm13h5f |
| Language | English |
| Publisher Date | 1974-09-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics Aerodynamic Drag Numerical Analysis Aerodynamic Configurations Skin Friction Pressure Distribution Hypersonic Flow Boundary Layer Transition Aerodynamic Coefficients Power Law Bodies Viscous Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
