Aerodynamic Shape Optimization of the X-37 Configuration for Improved Stability and Performance

摘要

The objective of this work was to apply numerical shape optimizations to the X-37 in order to improve its longitudinal stability and performance during descent. Wind tunnel test results for this vehicle, which were designed by Boeing at Seal Beach, California, showed longitudinal instability at Mach numbers between 0.6 and 1.5 and at moderate to high angles of attack. The instability was attributed to flow separation from the wing and tails. As part of the X-3 7 development program, Ames was requested to assist in refining this configuration through the use of numerical-optimization techniques developed under the High Speed Research Program.