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Jet-flapped airfoils in ground proximity

Sequence 46
42 APPENDIX A DERIVATION OF EQUATIONS (18), (19) The singular kernel in (14) may be removed by rewriting this equation in…
Sequence 47
43 Ie· If I ..:!L J?( J - ...:.L.. • (x) _ ~ ~ I } 1T J 2. ';1, (1r [M' (x.---r/{.-,,)] ) (A-4) As…
Sequence 48
The ground influence functions \ (x;x.,J.) and I,.('lCjXo,.«) take the form = {X(x-~1+4jI1 JI(x,J) - 2)., Xo Y(XI~) {X…
Sequence 49
45 , eoe J.. J~/-X i ~ ". )( x- Xo o CID I i I +.kf~ x • C; 'I.~(X){,j..J~/-"''' ell J…
Sequence 50
46 where IG and IT are given by (A-8) and (A-9). Except for the inclusion of nonsingular ground influence terms, equations (…
Sequence 51
APPENDIX B DOWNSTREAM ASYMPTOTIC BEHAVIOR OF JET FLAP The jet-flap shape and its associated vortex intensity far downstream…
Sequence 52
48 A physical restriction of finite lift limits our interest to the case ~> I That ~.(X) actually has the limiting form O…
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~----~~-------- DeJager (Ref. 13) shows 0(1..£) i f (3 00 is integer J Jx 'Xo~ '( fJ f X - )(0 } "…
Sequence 54
50 Having established ~ 4, the asymptotic behavior of the jet flap as X-+oo is given by ~, "()() = o (~4) I O(~) X…
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51 APPENDIX C DERIVATION OF EQUATIONS (50~) (SOb) Starting with equations (40a) through (43b) the trigonometric…
Sequence 56
52 be replaced by; Jet Flap Deflection 11 ®( ~ I 6,.) = co:s(,j':' f t;. «(9) { ( (9; eO) ~ ) SIN $ J<s o…
Sequence 57
Camber 11 e( C; J tj.) - co:s(!'Ji;-f ~ (aa) I(;o (6) j C5l. ) P.) sl~CJA9 o ii" ~(r;"JG,) :: SIN(1J* f…
Sequence 58
54 Since each of the four sets of equations (C-3a,b), (C-4a,b), (C-5a,b), (C-6a,b) are of the same form, each set may be…
Sequence 59
55 11- -I- 2.S'N(5a.)~ji\-LfCo~2.(~)cos~'P &cp To 2./11'" co. cp - Cos CPo o 11- +- 2 S'N…
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'il'- + .2 COS(~).!..JC.os......,,<prc;.(<p ;l30 ,j )St ... (t)Jcp ;-rn:: 1)2" .. Z. 1"1'…
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57 APPENDIX D A FLAT PLATE AIRFOIL IN GROUND PROXIMITY In Reference 8, Strand and Brainerd develop an approximate technique…
Sequence 62
58 where for the first iteration (0) K~ (X) is taken to be the away-from-ground solution, i.e. (01 ~<.J (X 1 H-x 20…
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59 -rr Finally, operating on (D-S) with ~ J [ ] c.oS ""m<So J~ and inter- o changing orders of integration,…
Sequence 64
60 The integrations in CD-8) must be carried out numerically. For (Il (I) various values of h the first iterative results…
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The above results are plotted in Figure D-l along with the exact nonlinear potential flow results of References 3, 4 and 19.…
Sequence 66
, " ,~ .. , CD. - J CO II 'f P :::> /. " 62 V. "! .c. 0, ti: 0: IJJ 0 Z <{ 0::: « w…
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63 APPENDIX E CAMBER AND THICKNESS EFFECTS ON AIRFOILS IN GROUND PROXIMITY The approximate technique used in Appendix D may…
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64 The mathematical procedures for finding the first iterative solution \..- (I) Ow (X) of (E-2) are identical to those of…
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-~------~~~~-- 65 Fig. E .. I Lift Coefficient due to Camber and Thickness ( Iterative Solution )
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66 I.. o ti 0:: ' . ... "1'l"KlIl:HH o
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