IP distributions using the FP3 which is the same as FPl except 8 Net propeller lift distribution-FP4.ДЄngle of attack ag. 7 Net propeller lift distribution-FP3.ДЇig. 10 Sectional lift distribution for Joukowski airfoilДЇig. It is expected that more drastic variations between the twoД¬alculations, classical and present theory, will be exhibited asДЄ consequence of an increase in S = Uj/u0 or an increase in theДЇig. Shows an overestimate of the classical calculations by 20%. Hand, the effect on propeller lift as shown in Fig. Increases as s/rj increases the overall effect due to the presentД¬orrection becomes proportionately smaller. The contribution to the total liftL = J-s/Cj) dy due to wing Where the span-to-propeller ratio has been doubled. 5, these calculations are repeated for the FP2 case Nonuniform corrections of the present theory are ignored. Is overestimated by close to 20 % in this calculation when the The effect of nonuniformities in the interaction of a propeller and a finite wing is investigated here using the step It can be seen that the total propeller lift is defined by Wind alone I0(y) from the sectional lift l(y) is shown in Fig. 4 Net propeller lift distribution-FPl.Д«ution lp(y) which is obtained by subtracting the lift of the Lift distribution as obtained by taking nonuniformities intoД¬onsideration will be presented for wings of finite span.ДЇig. In subsequent sections, a comparison between the lift distribution based on uniform aerodynamic coefficients and the With c0 the maximum chord and CLo the lift coefficient due toДЈ) The downwash in terms of the nondimensional quantity Where F is the total circulation and F 0 is the circulation due toДў) The net propeller lift lp(y) in terms of the difference in The numerical examples show that the modifications due to the use of more realistic two-dimensional analysis are significant.ДЎ) The circulation T in terms of the variable Uniform, and without distinct boundary, the sectional two-dimensional analysis is computed numerically by aДЇinite-difference scheme, while in the three-dimensional analysis of downwash, the propeller stream is replacedД«y an equivalent circular cylindrical jet of uniform velocity. When the oncoming propeller stream is not Velocity propeller stream in the calculation of the sectional lift. With the outer stream the modification is now* made to take into consideration the finite height of the higher When the Oncoming propeller stream is uniform and with a distinct boundary For the section inside the propeller stream, classical analysis assumes that the sectional height of the The basic assumptions of classical analysis have been retained except the one for the two-dimensional sectionalДЄnalysis. The effect of a single propeller on the aerodynamic characteristics of a high aspect ratio wing has been studied. Application of Airfoil Theory for Nonuniform Streams toДownloaded by UB Giessen on Janu| | DOI: 10.2514/3.44327

Thin airfoil theory assumptions