1. 3-5 provide additional experimental data. However, unlike their use in Reference 1, they cannot be used i n this study. Their Mach range and gap heights were covered and used for the range of interest of Reference 1.
2. Some earlier analytic work was done, primarily for supersonic speeds. This work usually neglects VlscoSity effects, which are very dominant for the small gaps, and also neglect the fin-body support effects. The present analysis avoids these two difficult-to-predict phenomena by utilizing measured data where these effects are hoth inc 7uded. Rleviss and %ruble 6 i n 1953 presented an inviscid analysis of gap losses for triangular fins i n supersonic speeds. The analysis i s only valid for triangular fins and neglects viscosity effects. It also assumes a long afterbody extending beyond the fin location. Mirles,' almost at the same time, presented a slender body analytic solution for the f i n lift losses for the same limitation of triangular fin, long afterbody behind the fins, no viscosity and no f i n support interference. Dugan and Hikido,a shortly after i n 1954, presented a slender body analysis for gap effects for triangul a r fins mounted on long afterbodies with no viscosity or f i n support interference effects considered. A more recent analytic work was done by Aligust 9 i n 19R2, who used the inviscid supersonic analysis of RlevisS and Struble and the manipulated ambiguous results of Hoernerlo at subsonic speeds, t o estimate the normal force losses for streamwise gaps. The application was made t o the typical triangular fin of aspect ratio 1.0. August applied the analysis t o the Sidewinder missile geometry a t M = 2.5 for the triangular canard f i n with f i n deflection. The gap area was estimated and equalized by a streamwise gap area. This application was done during the development of a fast aerodynamic design code. Sun, et al," i n 1984, re-iterated the results of August and made an application t o a missile configuration at M = 1.2 and 2.0 using the same computer code. In both cases of
3. (M = 1.2-4.0).
4. A 1. Large Gaps, Transonic Speeds (M = 0.8-1.2).