76 



ll^MR()|)^ \ VMics IN SHIP nisi{;N 



Sec. H.5 



TABLE 44jk — Bnoir Lwr of RcrcHKNccii Illl'stiutinc; Pui.kk DuniiAMti and Lirr/DRAa Ratios roR Airfoils 



AND IlrDROFOIlA 



assemblies are almost always of symmetric 

 section. The data presented or referenced here 

 represent only a small part of tlio.se available in 

 the technical literature but tliej' serve to indicate 

 about what may be expected as to tlic l)ehavior 

 of these assemblies. 



Fig. 44. C, adapted from a previous presentation 

 of the same rlata by K. 10. Schwiiherr (l'X.\, 1!)3!>, 

 Vol. II, pp. -JOS 20!)], Rives praplis of lift ciK-irMient 

 C't, for n HoricH of compound liydrofolLs with (laps 

 of varying length. Tlie iiydrofoil assembly as 

 le«le<l at Gottingen ("lOrgebnisso der Aorody- 



namischen Versuchsanstalt zu Cottinncn, III, 

 Licferung; Messungen an drei Ilohenleitwerkcn 

 (Results of Tests at the Aerodynamic Research 

 In.stitute, (Jottingen, Vol. Ill; Mea.suroments on 

 Three Flap Assemblies)," Munich and Hcrlin, 

 1'.)'27, pp. 10'-'-1071 had tlie general plnnform of 

 an airplane wing, with a nominal aspect ratio of 

 l()0/25 = 4.0 and a ratio byA„ = 4.301. The 

 three flap.s, measured from the trailing edge to 

 the hinge ccnt^T, had chord lengths of O.'JC), 0.3i), 

 and 0. IS limes tiie overall chord. The ratios of the 

 planform areas to the total plaMforn\ area were 



