(I guess I work on this blog for a short while every 4 years. It's not that I've lost interest in the subject, it's that life keeps getting in the way. I will try to do better!)
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The missing "Ca" (?) brought up the need to develop a wing area in which the entire assembly would produce a good polar curve (?), that is, one that would achieve low air resistance. This would be a better areodynamic state in which the pressure point would be constant in the total unit as far as possible. In this way the requirements of the control mechanism could be simplified. Each rotationally symmetrical elongated body without built up surfaces has a pressure point hike between subsonic and supersonic speeds. Also, bodies that are equipped with a tail in the rear, like the A-4, show this pressure point hike (see diagram Abb. 6) which requires proportionately large marginal control forces.
There the aerodynamic moment controls itself by normal forces of the unit and the [air force lever arm] acting together, and as such the control mechanism must be designed to employ maximum leverage on the air rudder.
There the aerodynamic moment controls itself by normal forces of the unit and the [air force lever arm] acting together, and as such the control mechanism must be designed to employ maximum leverage on the air rudder.
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