Aerodynamic characteristics of a canard-controlled missile at high angles of attack
| Autor: | Max F. Platzer, Edmund H. Smith, Sheshagiri K. Hebbar |
|---|---|
| Rok vydání: | 1994 |
| Předmět: |
Physics
Fin business.industry Angle of attack Longitudinal static stability Aerospace Engineering Aerodynamics Structural engineering symbols.namesake Missile Mach number Deflection (engineering) Space and Planetary Science symbols business United States Air Force Stability and Control Digital DATCOM Test data |
| Zdroj: | Scopus-Elsevier |
| ISSN: | 1533-6794 0022-4650 |
| DOI: | 10.2514/3.26510 |
| Popis: | A low-speed wind-tunnel investigation was conducted to examine the aerodynamic characteristics of a one-thirdscale model of a canard-controlled missile at high angles of attack using force and moment measurements. The data were taken at a nominal Mach number of 0.2 for angles of attack up to 50 deg at three different canard deflection settings. The test runs were limited to 0and 45-deg missile roll angles (symmetric configurations) and two sets of tails (aft fins), one with the full area including the roll damping tabs (rollerons) and the other without the rollerons. The data indicate that the rollerons act as an effective fin area at low speeds and high angles of attack, and make the missile more stable. The test data were also used to validate the aerodynamic characteristics of the missile as predicted by the Missile Datcom program. The agreement between the Datcom predictions and the test data is fairly good, with the latter indicating a slightly higher static stability. |
| Databáze: | OpenAIRE |
| Externí odkaz: |
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