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Correlation of transonic-cone preston-tube data and skin friction. [characterizing the flow quality of a transonic wind tunnel
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Reed, T. D. |
| Copyright Year | 1981 |
| Description | The distribution of Preston tube pressures within turbulent boundary layers along the surface of a sharp-nosed, ten degree cone was correlated with theoretical values of turbulent skin friction for freestream Mach numbers less than one. The mini-basic computer code, the Wu and Lock computer code, and the STAN-5 computer code were used to analyze the data and to solve the boundary layer conservation equations. The skin friction which results from using Preston tube pressures in the correlation equation, has a rms error of 1.125 percent. It was found that the effective center of the probe is not a constant but increases as the surface distance increases. For a specified unit Reynolds number, the effective center of the probe decreases as the Mach number increases. The variation of the fluid (air) properties across the face of the probe may be neglected for subsonic flows. The possible transverse errors caused by the use of the concept of a virtual origin for the turbulent boundary layer were investigated and found to be negligible. |
| File Size | 4074419 |
| Page Count | 148 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820007146 |
| Archival Resource Key | ark:/13960/t1zd2r848 |
| Language | English |
| Publisher Date | 1981-10-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Speed Indicators Skin Friction Transonic Wind Tunnels Fluid Flow Pressure Distribution Turbulent Boundary Layer Pitot Tubes Computer Programs Tables Data Cones Least Squares Method Boundary Layer Transition Data Correlation Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
