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Preliminary study of supersonic-transport configurations with low values of sonic boom
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Dugan Jr., J. F. |
| Copyright Year | 1973 |
| Description | A parametric study of low-boom supersonic transport airplanes with conventional configurations was made to identify the features of specific configurations that promise relatively low sonic boom overpressures (less than 47.9 N/sq m). The range of values considered was gross weight from 28,300 to 170,000 kg; cruise Mach numbers of 2 to 3.2; and wing loadings of 1436, 2870, and 4309 N/sq m. Fuselage length was varied from 49.1 to 102.4 m and fuselage diameter from 2.75 to 3.98 m. A nominal Mach 2 configuration weighing 56,700 kg and having a wing loading of 2870 N/sq m was selected; and its gross geometric, aerodynamic, and structural features were estimated. At a cruise altitude of 18,300 m, lift-drag ratio was estimated to be 7.35, while sonic boom overpressure was 41.7 N/sq m. Takeoff thrust loading using four afterburning turbojet engines at maximum dry thrust was 0.32. Payload for a 4440-km range was 16.7 percent of gross weight, giving a direct operating cost of 0.82 cent per seat statute mile. |
| File Size | 2456767 |
| Page Count | 37 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19730009312 |
| Archival Resource Key | ark:/13960/t54f6jq9j |
| Language | English |
| Publisher Date | 1973-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Supersonic Aircraft Cost Estimates Overpressure Transport Aircraft Lift Drag Ratio Feasibility Sonic Booms Aerodynamic Forces Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
