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Free-flight tests at Mach numbers from 0.8 to 1.4 to determine the effect on zero-lift drag of increasing the leading-edge bluntness of a 45 degree sweptback wing having an NACA 65A009 airfoil
| Content Provider | University of North Texas |
|---|---|
| Author | Pepper, William B. Jr. |
| Organization | Langley Aeronautical Laboratory |
| Description | Report presenting rocket-propelled models flown at transonic and supersonic speeds to determine the effect on zero-lift drag of increasing the leading-edge bluntness of a sweptback wing. Results regarding the total drag coefficient, wing-plus-interference drag coefficients, and force-break Mach number are provided. |
| File Format | |
| Archival Resource Key | ark:/67531/metadc59329 |
| Language | English |
| Publisher Date | 2018-03-27 |
| Access Restriction | Open |
| Subject Keyword | aircraft drag wing bluntness aircraft wings |
| Content Type | Text |
| Resource Type | Report |