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Transonic flow theory of airfoils and wings
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Garabedian, P. R. |
| Copyright Year | 1976 |
| Description | There are plans to use the supercritical wing on the next generation of commercial aircraft so as to economize on fuel consumption by reducing drag. Computer codes have served well in meeting the consequent demand for new wing sections. The possibility of replacing wind tunnel tests by computational fluid dynamics is discussed. Another approach to the supercritical wing is through shockless airfoils. A novel boundary value problem in the hodograph plane is studied that enables one to design a shockless airfoil so that its pressure distribution very nearly takes on data that are prescribed. |
| File Size | 537890 |
| Page Count | 10 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770003409 |
| Archival Resource Key | ark:/13960/t9x10w89p |
| Language | English |
| Publisher Date | 1976-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Boundary Value Problems Transonic Flow Fluid Dynamics Reynolds Number Wind Tunnel Tests Pressure Distribution Fuel Consumption Supercritical Wings Commercial Aircraft Aerodynamic Characteristics Prediction Analysis Techniques Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |