The Effects of Static Margin and Rotational Damping in Pitch on the Longitudinal Stability Characteristics of an Airplane as Determined by Tests of a Model in the NACA Free-flight Tunnel PDF Download
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Author: John P. Campbell Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 26
Book Description
Summary: The effects of static margin and rotational damping in pitch on the longitudinal stability characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rotational damping in pitch was varied over a wide range by using horizontal tails that varied in area from 0 to 24 percent of the wing area. A range of static margins from 2 to 16 percent of the mean aerodynamic chord was covered in the tests. For each test condition the model was flown and the longitudinal steadiness characteristics were noted. It was found in the investigation that longitudinal steadiness was affected to a much greater extent by changes in static margin than by changes in rotational damping. The best longitudinal steadiness was noted at large values of static margin. For all values of rotational damping, the steadiness of the model decreased as the static margin was reduced. The model was especially unsteady at low values of static margin (0.03 or less). Reduction in rotational damping had little effect on longitudinal steadiness, except that with low values of static margin (0.03 or less) the longitudinal divergences were sometimes more violent with the tailless (low rotational damping) condition.
Author: John P. Campbell Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 26
Book Description
Summary: The effects of static margin and rotational damping in pitch on the longitudinal stability characteristics of an airplane have been determined by flight tests of a model in the NACA free-flight tunnel. In the investigation, the rotational damping in pitch was varied over a wide range by using horizontal tails that varied in area from 0 to 24 percent of the wing area. A range of static margins from 2 to 16 percent of the mean aerodynamic chord was covered in the tests. For each test condition the model was flown and the longitudinal steadiness characteristics were noted. It was found in the investigation that longitudinal steadiness was affected to a much greater extent by changes in static margin than by changes in rotational damping. The best longitudinal steadiness was noted at large values of static margin. For all values of rotational damping, the steadiness of the model decreased as the static margin was reduced. The model was especially unsteady at low values of static margin (0.03 or less). Reduction in rotational damping had little effect on longitudinal steadiness, except that with low values of static margin (0.03 or less) the longitudinal divergences were sometimes more violent with the tailless (low rotational damping) condition.
Author: Langley Aeronautical Laboratory Publisher: Hassell Street Press ISBN: 9781013991097 Category : Languages : en Pages : 26
Book Description
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Author: Publisher: ISBN: Category : Aeronautics Languages : en Pages : 690
Book Description
Reproductions of reports, some declassified, of research done at Langley Memorial Aeronautical Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.
Author: John P. Campbell
Author: John P. Campbell
Author: John P. Campbell
Author: Langley Aeronautical Laboratory
Author: 
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: 
Author: United States. National Advisory Committee for Aeronautics