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Application of numerical optimization to the design of advanced supercritical airfoils
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hicks, R. M. Johnson, R. R. |
| Copyright Year | 1979 |
| Description | An application of numerical optimization to the design of advanced airfoils for transonic aircraft showed that low-drag sections can be developed for a given design Mach number without an accompanying drag increase at lower Mach numbers. This is achieved by imposing a constraint on the drag coefficient at an off-design Mach number while minimizing the drag coefficient at the design Mach number. This multiple design-point numerical optimization has been implemented with the use of airfoil shape functions which permit a wide range of attainable profiles during the optimization process. Analytical data for the starting airfoil shape, a single design-point optimized shape, and a double design-point optimized shape are presented. Experimental data obtained in the NASA Ames two-by two-foot wind tunnel are also presented and discussed. |
| File Size | 501274 |
| Page Count | 11 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19790011878 |
| Archival Resource Key | ark:/13960/t9w13vz92 |
| Language | English |
| Publisher Date | 1979-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Structural Design Aerodynamic Drag Numerical Analysis Airfoil Profiles Supercritical Wings Aerodynamic Coefficients Optimization Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
