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A simple analytical aerodynamic model of langley winged-cone aerospace plane concept
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Pamadi, Bandu N. |
| Copyright Year | 1994 |
| Description | A simple three DOF analytical aerodynamic model of the Langley Winged-Coned Aerospace Plane concept is presented in a form suitable for simulation, trajectory optimization, and guidance and control studies. The analytical model is especially suitable for methods based on variational calculus. Analytical expressions are presented for lift, drag, and pitching moment coefficients from subsonic to hypersonic Mach numbers and angles of attack up to +/- 20 deg. This analytical model has break points at Mach numbers of 1.0, 1.4, 4.0, and 6.0. Across these Mach number break points, the lift, drag, and pitching moment coefficients are made continuous but their derivatives are not. There are no break points in angle of attack. The effect of control surface deflection is not considered. The present analytical model compares well with the APAS calculations and wind tunnel test data for most angles of attack and Mach numbers. |
| File Size | 1356331 |
| Page Count | 45 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19950005762 |
| Archival Resource Key | ark:/13960/t9x111f6h |
| Language | English |
| Publisher Date | 1994-10-01 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Design, Testing And Performance Aerodynamic Drag Pitching Moments Aerospace Planes Hypersonic Speed Subsonic Speed Supersonic Speed Aerodynamic Coefficients Mathematical Models Angle of Attack Hypersonic Aircraft Mach Number Lift 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 |
