Abstract
Summary
The method which was developed in an earlier paper for calculating the
lift on a thin jet-flapped aerofoil has been applied to the case in which
the jet enters the main stream tangentially from a deflected flap. The lift
derivative with respect to the (small) angle of deflection β is of the
form
where ,
E being the ratio of flap length to aerofoil
chord, and D0 a function
both of E and of the jet momentum coefficient
CJ. In the special
case CJ = 0,
Do vanishes and the
classical results for attached flow on flapped aerofoils without
super-circulation are obtained. More generally,
Do has been
evaluated over the range
0<CJ<5 for six
ratios E between 0·02 and 0·50, using an
electronic computer. The lift derivatives so found lie between those in the
limiting cases of “deflection” (E = 0) and “incidence” (E=1) which were
calculated in Reference 1. They show that the effectiveness of the jet-flap
scheme might be greatly increased by blowing over flaps of the order of 20
or 30 per cent of the chord, rather than over the small “shrouds” which have
hitherto been proposed.
Publisher
Cambridge University Press (CUP)
Reference4 articles.
1. Maskell E. C. and Gates S. B. Preliminary Analysis
for a Jet-Flap System in Two- Dimensional Inviscid Flow. A.R.C. Current
Paper 359, June 1955.
2. Glauert H. Theoretical Relationships for an Aerofoil
with a Hinged Flap. R. & M. 1095, April
1927.
3. The lift coefficient of a thin, jet-flapped wing
Cited by
21 articles.
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