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Comparison of experimental and theoretical zero-lift wave-drag results for various wing-body-tail combinations at mach numbers up to 1.9
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1957 |
| Description | Comparisons are made of experimental and theoretical zero-lift wave drag for several nose shapes, wing-body combinations, and models of current airplanes at Mach numbers up to 1.0. The experimental data were obtained from tests in the Ames 6- by6-foot supersonic wind tunnel and at the NACA Wallops Island facility. The theoretical drag was found by use of linear theory utilizing model area distributions. The agreement between theoretical and experimental zero-lift wave-drag coefficients was generally very good, especially for a fuselage or for fuselage-wing combinations that were vertically symmetrical. For other models that had rapid changes in body shape and/or were not vertically symmetrical, the agreement of theory with experiment ranged from fair to poor, depending on the severity of the change in shape. |
| File Size | 3008091 |
| Page Count | 51 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19660010455 |
| Archival Resource Key | ark:/13960/t11p2td7q |
| Language | English |
| Publisher Date | 1957-03-27 |
| Access Restriction | Open |
| Subject Keyword | Drag Coefficient Nose Cone Zero Lift Wing Body Wave Drag Tail Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
