Design, Analysis and Research Corporation (DARcorporation) ERRATA: Airplane Flight Dynamics and Automatic Flight Controls Part I

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1 Design, Analysis and Research Corporation (DARcorporation) ERRATA: Airplane Flight Dynamics and Automatic Flight Controls Part I Copyright 00 by Dr. Jan Roskam Year of Print, 00 (Errata Revised August 7, 08) Please check the website for updated errata page iii, line 3 page x, line 4 page xxii xxviii Topic 3..7 Review of Important Sign Conventions should be removed The second word control in the description of the cl should be deleted Add the following symbols and descriptions Symbol Description Unit page xxii X, Y, Z Body-fixed (rotating) axis system -- page xxii X, Y, Z Earth-fixed (non-rotating) axis system -- page xxvi,, 3 Eular rotation sequence (the use of the symbol to denote the first Euler rotation is used only in Chapter ) page xxvii P Origin of the XYZ system page 4, Line 33 = 90) should be = 90 page 6, Equation (.6) = k should be = j page 8, Line 9 page 34, Line 5 page 40, Line 6 page 47, Line un should be in Should read Roskam, J.; Airplane Design, Parts I through VIII; Design, Analysis, and Research Corporation, 440 Wakarusa Drive Suite #500, Lawrence, KS 66049, USA; 990 Should read apply to cambered (un-symmetrical) airfoils. In variant should be invariant Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00

2 page 5, Line 0 top should be to page 55, Equation (.7) d d d d = M M = ( 0 M ) page 59, Figure.0 page 63, Line 8 Flap Chord, c f, should go from hinge line to trailing edge b) should be c) page 66, Figure 3. should be in Note 3 page 84, Equation (3.30) ( ) cos ( ) ( ) cos ( ) M = M + L x x L x x A acwf wf cg acwf h ach cg page 85, Line 9 page 95, Line 6 page 97, Figure 3.8 page 99, Figure 3.30 page 04, Line 30 page 06, Equation (3.67) page 08, Figure 3.38 as well a positive should be as well as positive Should read shed vortices (at high angles of attack) which Normal velocity vector on left wing should not be present Axis labeled as Z should be labeled as X right wheel deflection are activated should be right wheel deflection) are activated K SW needs to be defined: is the gearing constant between cockpit control wheel or stick and aileron or spoiler deflection The subscripts v should be taken out from the two variables Fa yrudder and N A rudder Sz v v page 08, Equation (3.7) C s l C = L r v r v Sb page 09, Equation (3.7) A = A = ( l + l a + l r ) L L C C C qsb s a r Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00

3 page, Equation (3.76) F A y L y C qs C d = = q v S v v v v d page 3, Equation (3.78) page 3, Equation (3.80) page 5, Line 4 page 7, Line 9 page 7, Line 8-9 page 8, Figure 3.46 page 8, Figure 3.46, Note The subscripts v should be taken out from the variables F a yrudder ( ) F = F = C + C + C qs A y A y y a y r s y a r Should read The yawing moment due to the vertical tail may be written as: After Line 9, should read Methods for computing the yawing moment due to aileron control derivative are found in Part VI of Reference 3.. Lines 8-9 should read Methods for computing the yawing moment due to spoiler control derivative are found in Part VI of Reference 3.. Positive rolling moment should be Positive yawing moment induces drag should be induced drag page, Equation (3.9) A = A = ( n + n a + n r ) N N C C C qsb s a r page, Equation (3.9a) i= n LT = L T = Ti ( zt cost sint yt sint ) cos i i i i i + s i = i= n + Ti ( xt cost sint yt cost cos T ) sin i i i i i i i = page, Equation (3.9b) i= n ( cos sin ) F F T = = Ty T i T T y i i i= Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00 3

4 page, Equation (3.9c) i= n NT = N T = Ti ( xt cost sint yt cost sint ) cos i i i i i i + s i = i= n Ti ( zt cost sint yt sint ) sin i i i i i i = page 4, Equation (3.95b) The summation should say i = page 6, Table 3.4 V should be Q page 7, Line 4 Should read ) partial derivatives in Table 3.4 indicate the slope by which a particular perturbed force or moment is affected by a particular perturbed variable. page 33, Figure 3.5 V P should be V p in all cases C page 34, Figure 3.5 arctan D 0 should be M M = M C arctan D 0 M M = M page 34, Figure 3.5 Caption should read Example of Determination of: CD / M at a constant angle of attack page 36, Equation (3.9) C Lu = M ( M ) C L M u U page 36, Equation (3.) ( m m ) A = C + C q Sc u F Az = L + D C C q S page 39, Equation (3.33) ( ) page 4, Equation (3.4) airplane, caused by should be airplane CL, caused by Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00 4

5 M page 45, Equation (3.56) A C = m qsc = Cm q qsc qc qc U U page 47, Equation (3.6) Replace the variable C L in (,) entry to C D page 47, Equation (3.6) c c should be U U page 48, Equation (3.63a) FA y = CyqS page 48, Equation (3.63b) LA = ClqSb page 48, Equation (3.63c) NA = CnqSb page 48, Line 7 changes in sideslip, should be changes in sideslip rate, page 48, Line 8 sideslip angle, should be sideslip rate, page 6, Equation (3.97) Cn p should be C n p page 6, Equation (3.97) Cn r should be C n r page 67, Equation (3.4) n p 550 pbhp F Tx = U + u page 73, Line 7 page 8, Line Should read normally sufficiently small that they can be neglected Should read Roskam, J.; Airplane Design, Parts I through VIII; Design, Analysis, and Research Corporation, 440 Wakarusa Drive, Lawrence, KS 66049, USA; 990 page 8, Line 6 Should read Lan, C.E. and Roskam, J.; Airplane Aerodynamics and Performance; Design, Analysis, and Research Corporation, 440 Wakarusa Drive, Lawrence, KS 66049, USA; 990 page 86, Equation (4.3) ( Tx Du ) ( Tx D ) C C C C u + 0 Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00 5

6 ( ) MA+ MT page 87, Table 4. Entry (5,5), ( MA+ MT) 0 0 should be page 89, Equation (4.7) A + T = y y ( y + Ty ) F F C C qs page 89, Line 3 (4.) should be (4.6) page 90, Line 6 criterion (4.) should be criterion (4.0) page 90, Line CZ C T L should be CT z CL page 95, Line 6 Table 5. should be Table 4. page 96, Line Table 5. should be Table 4. page 06, Line 8 in Example. should be in Example ). page 09, Figure 4.b page, Line page, Line page 6, Line 5 page 0, Equation (4.8) The negative tail stall locus as shown in the diagram is wrong. The trim diagram should have a positive tail stall locus at = 5 and a negative tail stall locus at = -. Both of these lines are out of the range of the diagram so none of them should be shown. The sentence that reads, Figure 4.b shows only the negative tail stall locus because the positive locus is outside of the diagram should be removed degespectively should be deg respectively Appendix A.. should be Appendix A. Vmc = ( N + N ) T D C n r rmax Sb page 5, Equation (4.86b) Rb mur mg sin = Cy + Cy + C r y a + C y r q S U a r page 5, Line 0 three of these should be four of these Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00 6

7 g tan page 6, Equation (4.90) = U page 6, Line 8 page 7, Equation (4.96) Should read By combining Eqns (4.85b) and (4.85c) with Rb 0 = Cy + Cy + C r y a + C y r q S U a r page 7, Equation (4.97) should be page 7, Equation (4.03b) should be page 7, Equation (4.03c) should be page 7, Line 6 The first sentence should be removed. page 8, Equation (4.98) Variables a, b and c should be a, b and c page 8, Equation (4.99) Variables a, b and c should be a, b, and c page 8, Equation (4.00) Variables a, b and c should be a, b, and c page 8, Equation (4.00) a should be r page 8, Equation (4.0a) should be page 8, Equation (4.0b) should be page 8, Equation (4.0c) should be page 8, Equation (4.0a) a should be a page 8, Equation (4.0b) b should be b page 8, Equation (4.0c) c should be c page 3, Equation (4.3b) should be Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00 7

8 page 3, Equation (4.4a) should be page 33, Line forward should be aft page 34, Figure 4. Arrow for M ac wf should act on the A.C. of the wing-fuselage not the C.G. page 35, Line 4 page 37, Equation (4.3) conventional should be canard ( ) ( ) + ( ) = 0 L x x L x x M L x x c cg acc wf acwf cg acwf h ach cg page 37, Line 7 in Eqn (4.0) should be in Eqn (4.3) page 37, Lines 0- Should read From Eqn (4.33) it may be concluded that as long as L h is positive (i.e. up) and ( xac xcg ) is wf positive the canard load to trim, L c, will also be positive (i.e. up). page 4, Equation (4.36) HM = ChqhSece page 44, Line 7 q q h = should be h h = qh q page 53, Line 3 found by by should be found by page 55, Line 0 from Eqn 4.69) should be from Eqn (4.69) page 59, Figure 4.36a e = should be t e = df page 59, Figure 4.36b e dv should be s df dv page 63, Line page 67, Line 0 page 67, Line page 67, Line 4 Should read Next, recall the stick-force equation positive should be negative positive should be negative negative should be positive Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00 8

9 page 68, Line 4 Include in r definition: r negative = and is normally r Ch page 69, Equation (4.99) v Cn = Cn + Cn free fix r Ch r page 69 Equation (4.03) F G q S c C r = C r v r r h r n r C n free page 73, Line 4 page 78, Line 6 page 78, Line page 78, Line 6 Should read or, with Eqn (4.08) as: Should read HM is the elevator hinge moment as expressed by Eqn (4.36) Should read, The hingemoment coefficient equation Equation 4.5 should be 4.5a page 80, Line 6 e n F should be s n page 8, Line 0 Should read moment and stick-force trim. This represents page 8, Line List is inconsistent with Figure 4.49 page 86, Equation (4.4) Ch should be Ch r v page 88, Line 3 page 88, Line 5 Should read Exceptions to this are airplanes like the B-5. Should read at the instant of rotation: no load on the nose-gear. page 88, Equation (4.45) Dg = CD q g rotates page 88, Line 7 C D ground should be C D g page 90, Equation (4.46) L wf = g C Lwf q rotate S g Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00 9

10 page 90, Line 3 C L wfground should be C L wfg page 90, Equation (4.47) L h = g C L h hg q rotate S h g page 90, Line 6 C L hground should be C L hg page 90, Equation (4.48) M ac = wf C mac q rotate Sc g wf g page 90, Line 8 C m should be acwfground C m acwfg page 9, Line 4 page 9, Equation (4.50) are should be area should be mg page 9, Equation (4.50) C L maxhground should be C L maxhg page 9, Table 4.0 C D ground should be C D g page 9, Table 4.0 C L wfground should be C L wfg page 9, Table 4.0 C L maxhground should be C L maxhg page 9, Table 4.0 C m acwfground should be C m acwfg page 9, Figure 4.5b xcg g = 38 ft should be xcg g = 39 ft and vice versa page 305, Figure 5. t should be t 0 in all cases page 307, Equation (5.a) page 307, Equation (5.b) u u mu = mgcos + qs ( CD + CD ) + ( CT + C u x T U x ) + u U ( CD CL ) CD e e Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00 0

11 page 307, Equation (5.c) page 34, Figure 5.6 page 36, Line 9 u ( ) sin ( L L ) ( L D ) m w Uq = mg + qs C + C C + C + u U c qc CL CL CL e U q U e u I q = q Sc C + C + C + C + C + C + u ( ) ( ) yy mu m m m m m U T u T U T c qc + Cm + Cm + Cm e U q U e Solid black line should be removed the system is zero should be the system are zero page 38, Line 5 Should read First, by using the substitution q = and w= U qsc Cm page 39, Table 5. M = IyyU should be qsc Cm M = IyyU page 3, Equation (5.35) page 34, Line 6 Equation for B u should read: ( ) ( ) B = X U Z M + Z + M U + Z + Z X u e q q e Should read Response of the airplane to control page 38, Equation (5.48) Cm C m u C + C C + C L D Lu L m page 38, Equation (5.49) ( xcg x ) C C m = u ac A L L + u L C C C page 33, Equation (5.53) s,, n j, n,, s sp = spn jn sp sp sp = or page 333, Equation (5.54) 3,4 3,4n j 3,4 n3,4 3,4 s = or Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00

12 s ph = phn jn ph ph ph page 333, Line 8 Should read T = 0.35sec and T = 0.8 sec page 333, Equation (5.56) page 338, Equation (5.69) page 340, Line 3 3,4 3,4n j 3,4 n3,4 3,4 s = or 3 rd = 3 rd n jn 3 rd 3 rd 3 rd s () s = () s ration should be ratio e ( Z s XuZ + X Zu) e e e gz U s Xus U u page 340, Equation (5.76) u( t) page 340, Equation (5.77) ( ) page 340, Equation (5.78) ( t) lim lim e Nu = s =... s 0 s D t lim lim e N t s = =... s 0 s D t lim lim e N s = =... s 0 s D t page 34, Equation (5.8a) page 34, Equation (5.8b) page 34, Equation (5.8b) page 34, Equation (5.8c) ps n sp ps n sp should be ps np should be ps np should be s n n ps n sp should be ps np page 350, Line 5 ( s) / ( s) should be ( s) / ( s) e Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00

13 page 364, Line 8 Eqn (5.0) should be Eqn (5.) page 37, Equation (5.36) ( t) page 37, Equation (5.37) ( t) page 37, Equation (5.38) ( t) lim lim a N = s =... s 0 s D t lim lim a N = s =... s 0 s D t lim lim a N = s =... s 0 s D t page 38, Figure 5.4 page 38, Figure 5.5 page 38, Figure 5.6 page 38, Figure 5.7 page 384, Figure 5.8 page 384, Figure 5.9 page 385, Figure 5.30 page 385, Figure 5.3 page 387, Figure 5.3 page 387, Figure 5.33 page 388, Figure 5.34 page 388, Figure 5.35 page 390, Figure 5.36 page 390, Figure 5.37 page 39, Figure 5.38a page 39, Figure 5.38b Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00 3

14 page 393, Figure 5.39 page 393, Figure 5.40 page 394, Figure 5.4 page 394, Figure 5.4 page 396, Line 5 page 398, Line page 40, Figure 5.44 Should read say 0 deg/deg/sec, a 3 deg/s pitch rate elevator deflection should be rudder deflection On the Y B vector, the smaller vector should be labeled q page 405, Lines 4-8 Remove paragraph contained by lines 4-8 page 407, Line 4 cos = 0 should be cos = page 44, Table 6.4 The Civilian Requirements FAR-3 are updated to the following: For wheel controllers: ( ) F s W TO and n n n limit limit limit 50.0 but not more than: n For stick controllers: Fs n W 5.0 TO and 40 n limit 35.0 but not more than: n limit page 47, Line 6 page 47, Line 7 Remove the return so be and written are on the same line. time to double should be time-to-double page 434, Line Reference 6.5 should be Reference 6.6 page 460, Line Should read Roskam, J.; Airplane Design, Parts I through VIII; Design, Analysis, and Research Corporation, 440 Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00 4

15 Wakarusa Drive Suite #500, Lawrence, KS 66049, USA; 990 page 46, Lines 0-3 page 466, Line 6 page 466, Line 9 Should read 440 Wakarusa Drive Suite #500, Lawrence, KS 66049, USA Tel Should read Design, Analysis, and Research Corporation, 440 Wakarusa Drive Suite #500, Lawrence, KS 66049, USA Should read Design, Analysis and Research Corporation, 440 Wakarusa Drive, Suite #500, Lawrence, KS 66049, USA Tel Appendix B Ch should be Ch r v for all examples page 480, Table B page 487, Table B page 50, Table B4 page 560, Line 8 C.G. location should be 0.64 c C.G. location should be 0.33 c C.G. location should be 0.7 c Should read Roskam, J.; Airplane Design, Parts I through VIII; Design, Analysis, and Research Corporation, 440 Wakarusa Drive Suite #500, Lawrence, KS 66049, USA; 990 Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 00 5

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