Editing Bachem Ba 349 Natter (section)

==Stability==
In early February 1945, the positions of the centre of gravity for the A1 operational machine during its flight profile were giving the RLM and the SS cause for concern. They wanted these figures to be decided upon for the upcoming construction of the A1 aircraft for ''Krokus-Einsatz'' (Operation Crocus), the field deployment of the Natter.<ref>''Aktenvermerk über eine Besprechung am 8-2-45, "Für die Flugeigenschaftsprüfung…" '' (in German). Berlin-Aldershof: DVL, February 1945.</ref> The position of the centre of gravity is expressed as a percentage of the chord (distance between the leading and trailing edges) of the main wing. Thus 0% is the leading edge and 100% is the trailing edge. In the manned glider trials the centre of gravity had been varied between 20 and 34%.

At a meeting of engineers held on 8 February, the variations in the centre of gravity expected in the A1 ''Krokus'' machine were discussed. At take-off with the weight of the four solid boosters, the centre of gravity would be brought back to 65%, but after releasing these rockets it would move forwards to 22%. The free flight by Zübert on 14 February had shown unequivocally that the little Natter had excellent flying characteristics as a glider. The centre of gravity problem was solved initially by the addition of one-metre-square auxiliary tailfins that were released simultaneously with the jettisoning of the boosters.<ref name="Millikan 1945, p. 14"/> The ''Krokus'' aircraft had vanes that would direct the Walter rocket exhaust gases so as to assist vehicle stabilisation at low speed similar to those used in the V-2 rocket.