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Computer programs for calculating pressure distributions including vortex effects on supersonic monoplane or cruciform wing-body-tail combinations with round or elliptical bodies
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Nielsen, J. N. Dillenius, M. F. E. |
| Copyright Year | 1979 |
| Description | Computer programs are presented which are capable of calculating detailed aerodynamic loadings and pressure distributions acting on pitched and rolled supersonic missile configurations which utilize bodies of circular or elliptical cross sections. The applicable range of angle of attack is up to 20 deg, and the Mach number range is 1.3 to about 2.5. Effects of body and fin vortices are included in the methods, as well as arbitrary deflections of canard or fin panels. |
| File Size | 23478356 |
| Page Count | 633 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19810018506 |
| Archival Resource Key | ark:/13960/t8hf2nc91 |
| Language | English |
| Publisher Date | 1979-04-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Cruciform Wings Missile Configurations Supersonic Flight Vortices Body-wing and Tail Configurations Pressure Distribution Leading Edges Computer Programs Aerodynamic Loads Axisymmetric Bodies Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
