Multifidelity Analysis and Optimization for Supersonic DesignSupersonic aircraft design is a computationally expensive optimization problem and multifidelity approaches over a significant opportunity to reduce design time and computational cost. This report presents tools developed to improve supersonic aircraft design capabilities including: aerodynamic tools for supersonic aircraft configurations; a systematic way to manage model uncertainty; and multifidelity model management concepts that incorporate uncertainty. The aerodynamic analysis tools developed are appropriate for use in a multifidelity optimization framework, and include four analysis routines to estimate the lift and drag of a supersonic airfoil, a multifidelity supersonic drag code that estimates the drag of aircraft configurations with three different methods: an area rule method, a panel method, and an Euler solver. In addition, five multifidelity optimization methods are developed, which include local and global methods as well as gradient-based and gradient-free techniques.
Document ID
20100042294
Acquisition Source
Langley Research Center
Document Type
Contractor Report (CR)
Authors
Kroo, Ilan (Stanford Univ. Stanford, CA, United States)
Willcox, Karen (Massachusetts Inst. of Tech. Cambridge, MA, United States)
March, Andrew (Massachusetts Inst. of Tech. Cambridge, MA, United States)
Haas, Alex (Stanford Univ. Stanford, CA, United States)
Rajnarayan, Dev (Stanford Univ. Stanford, CA, United States)
Kays, Cory (Massachusetts Inst. of Tech. Cambridge, MA, United States)