Abstract
The paper deals with optimum tail plane influence on drag and lift in trimmed flight and with the possibility of utilizing the lift and drag optimum center of gravity (c. g. ) range in designs of artificially stabilized aircraft. A simple relation of wing tail interference drag resulting from mutual vortex interactions is developed. Then, relations for minimum trimmed drag and for the drag optimum c. g. position are presented. It is shown how to design the tail plane so that the drag increase caused by c. g. deviation from the drag optimum c. g. position remains small. In regard to lift effects, it is shown how the maximum trimmed lift can be increased by full utilization of tail lift potential. Then, it is described that the usable c. g. range is determined by control requirements. Finally, it is examined how the optimum drag and lift c. g. range can be made compatible with the usable c. g. range determined by control requirements.
| Translated title of the contribution | Optimum Tail Plane Design for Artificially Stabilized Aircraft. |
|---|---|
| Original language | German |
| Pages (from-to) | 1-10 |
| Number of pages | 10 |
| Journal | Zeitschrift fur Flugwissenschaften und Weltraumforschung |
| Volume | 2 |
| Issue number | 1 |
| State | Published - 1978 |