Engineering topics

Hurley, F. X.

Publications and source records attributed to Hurley, F. X..

4 records

NASA NTRS1975

Detailed transonic flow field measurements about a supercritical airfoil section

The transonic flow field about a Whitcomb-type supercritical airfoil profile was measured in detail. In addition to the usual surface pressure distributions and wake surveys, schlieren photographs were taken and velocity vector profiles were determined in the upper surface boundary layer and in the near wake. Spanwise variations in the measured pressures were also determined. The data are analyzed with the aid of an inviscid transonic finite-difference computer program as well as with boundary layer modeling and calculation schemes.

Hurley, F. X.↗

NASA NTRS1975

Supercritical airfoil flowfield measurements

Detailed measurements in the transonic flowfield about a Whitcomb-type supercritical airfoil profile are presented including surface pressure distributions, far wake surveys, spark schlieren photographs, and a series of vector velocity profiles in the boundary layer and in the near wake. A flowfield composite for the transonic drag rise condition is constructed from these data. The boundary layer measurements are compared with current correlation and computation schemes, and the importance of viscous thickening effects is demonstrated by the results of wave drag rise calculations for the thickened and unthickened profiles.

Hurley, F. X.↗

NASA NTRS1975

Measured three-dimensional effects in transonic airfoil testing

An investigation was conducted regarding the issue of deviation from two-dimensionality in flowfield studies of a supercritical airfoil. It was found that significant three-dimensional effects occur in transonic airfoil tests, even for an aspect ratio of four. This is especially true at the supercritical Mach numbers, for which lateral propagation of disturbances is effective.

Hurley, F. X.↗

NASA NTRS1975

Miniature probe for transonic flow direction measurements

A miniature probe is developed for measuring flow direction in one plane as well as stagnation pressure in the boundary layer and near wake of a transonic airfoil. The probe tip geometry and calibration curves are given, along with near wake survey data obtained for a supercritical airfoil. The advantages of the probe are ruggedness, ease of fabrication, ability to measure flow direction at a point, and insensitivity to out-of-plane velocity components.

Spaid, F. W.↗