Print, 2001 - DARcorporation

Design, Analysis and Research Corporation (DARcorporation)ERRATA: Airplane Flight Dynamics and Automatic Flight Controls Part ICopyright © 1995 by Dr. Jan RoskamYear of Print, 2001(Errata Revised December 18, 2014)Please check the website www.darcorp.com for updated erratapage iii, line 3page x, line 4page xxii – xxviiiTopic 3.2.17 Review of Important Sign Conventions should beremovedThe second word ‘control’ in the description of the clδshould bedeletedAdd the following symbols and descriptionsSymbol Description Unitpage xxii X, Y, Z Body-fixed (rotating) axis system --page xxii X’, Y’, Z’ Earth-fixed (non-rotating) axis system --page xxvi 1, 2, 3 Eular rotation sequence (the use of thesymbol “1” to denote the first Euler rotationis used only in Chapter 1)page xxvii P Origin of the XYZ systempage 14, Section 1.4 Last paragraph, 1 st line “ Θ= 90) ” should be “ Θ= 90 ”page 26, Eq (1.62) First equation set “ ω = kΘ ” should be “ ω = j Θ 2 ”page 28, Line 9page 34, Lines 25-26page 40, Line 26page 47page 51“un” should be in.Reference should be: Roskam, J.; Airplane Design, Parts Ithrough VIII; Design, Analysis, and Research Corporation, 1440Wakarusa Drive Suite #500, Lawrence, KS 66049, USA; 1990Should read, “ apply to cambered (un-symmetrical) airfoils.”First paragraph under 2.5.2 second line. “In variant” should be“invariant”Second paragraph 8 th line. “top” should be “to”Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 2001 1

page 55, Eq (2.27)should be⎛ dε⎞dε⎜ ⎟⎛ ⎞ ⎝dα⎠⎜ ⎟ =dα⎝ ⎠M−M = 02( 1 M )page 59, Figure 2.20page 63, Problem 2.3Flap Chord, c f , should go from hinge line to trailing edgethe set of data under data set “a” should be data set “c”page 66, Figure 3.2 β should be β 1 in Note 3.page 84, Eq (3.30) in cos( α + − ε)“i W ” should be “i h ”i wpage 84, Eqn (3.30)page 85, Line 19The wing incidence should be removed“as well a positive” should be “as well as positive”page 95, Last Paragraph4 th line. After “vortices” add “(at high angles of attack)”page 97, Figure 3.28page 99, Figure 3.30page 104page 106, Eqn (3.67)page 108, Figure 3.38page 108 Eqn (3.71)page 109, Eqn (3.72)Normal velocity vector on left wing should not be present.Axis labeled as “Z” should be labeled as “X”.Last paragraph, last line “right wheel deflection are activated”should be “right wheel deflection) are activated”K SW needs to be defined: is the gearing constant between cockpitcontrol wheel or stick and aileron or spoiler deflection.The subscripts “v” should be taken out from the two variablesFa yrudderand N A rudderSz v vCsl Cδ L r vr α α δ ηv Sb= replaces SxC v vsl CrL qδ = αvα δrvSbmultiply right side quantity by qSbpage 111, Eqn (3.76) Should read: F A y L 1y C qS C ⎛ dσ⎞= β =− β q v S vv β v α v⎜ − ⎟⎝ dβ⎠Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 2001 2

page 113, Eqn (3.78)Equation (3.78), the subscripts “v” should be taken out from thevariables F a yrudderpage 113, Eqn (3.80)page 115, Line 14Equation (3.80) should be multiplied by: qS“The yawing moment due to the vertical tail me be written as:”should be “The yawing moment due to the vertical tail may bewritten as:”page 117, Line 20 Line 20 should be between Lines 13 and 14.page 118, Figure 3.46page 121, Eq (3.91)“Positive rolling moment” should be labeled as “Yawingmoment”.multiply right side quantity by qSbpage 122, Eqn 3.92a The summation should say i = 1page 122, Eqn 3.92b The summation should say i = 1page 122, Eqn 3.92c The summation should say i = 1page 127, Line 4Should read, “2) partial derivatives in Table 3.4 indicate the slopeby which a particular perturbed force or moment is affected by aparticular perturbed variable.”page 133, Figure 3.51 All “ VP 1” in this figure should be “ V p”page 134, Figure 3.52∂CD∂CDEquation “ arctan > 0 ” should be “ arctan∂M M = M∂M 2M = M2< 0Figure should be labeled “Example of Determination of:∂C/ ∂Mat a constant angle of attack”.page 136, Eqn (3.119) “ C L ” should be “ C L 1”page 136, Eqn (3.122) Variable M should be “M A ”D”.page 139, Eqn (3.133)Equation (3.133), change the subscript “x” to “z” in∂F Az∂αpage 141, Eqn (3.142) change “airplane, caused by” to “airplane, ∆CLcaused by”Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 2001 3

∂Mpage 145, Eqn (3.156) change A ∂C=mqS 1 = Cm qqS 1⎛ qc ⎞ ⎛ qc ⎞∂⎜ ⎟ ∂⎜ ⎟⎝2U1⎠ ⎝2U1⎠∂MA ∂C=mq1Sc = Cm qq1Sc⎛ qc ⎞ ⎛ qc ⎞∂⎜ ⎟ ∂⎜ ⎟⎝2U1⎠ ⎝2U1⎠topage 147Equation (3.162), replace the variableC L 1in (2,1) entry toC D 1α cα cpage 147, Eqn (3.162) “ ” should be “ ”2U12U1page 148, Eqn (3.163a,b,c)page 148, Section 3.2.10The negative signs should be removedFirst paragraph “changes in sideslip, β ” should be “changes insideslip rate, β ”Second paragraph “sideslip angle, β ” should be “sideslip rate, βpage 162, Eqn (3.197) “ Cn p ” and “ Cn r ” should be “ C np ” and “ C nr ,” respectively.page 167, Eq (3.214)page 173page 182, Lines2-3, 17-18Insert “+ u” in denominator.np550ηpBHPFT=xU + u1First paragraph, 5 th line. The word “be” is duplicated and should bedeletedReference should be: Roskam, J.; Airplane Design, Parts I throughVIII; Design, Analysis, and Research Corporation, 1440 WakarusaDrive, Lawrence, KS 66049, USA; 1990page 186 Equation (4.3), remove the variable U 1page 187Entry (5,5), change( M M )∂ A+∂αT> 0to( M M )∂ A+∂αT< 0page 189Equation (4.7), remove the negative signpage 189 The line below Equation (4.7), change (4.1) to (4.6)page 190 Line 6, “criterion (4.1)” should be “criterion (4.10)”Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 2001 4

page 190 Line 11, CZ T CLshould be α αCT z CLα αpage 195 Equation (4.36), remove the variable U 1page 195, Line 6 “Table 5.1” should be “Table 4.1”.page 196, Line 2 “Table 5.1” should be “Table 4.1”.page 206page 209, Fig 4.11bpage 211, 11 th linepage 211, 11 th linepage 216, 15 th lineLast paragraph, 3 rd line, “in Example 1.” should be “inExample 1).”The negative tail stall locus as shown in the diagram is wrong. Thetrim diagram should have a positive tail stall locus at α = 25 0 and anegative tail stall locus at α = -12 0 . Both of these lines are out ofthe range of the diagram so none of them should be shown.The sentence that reads, “Figure 4.11b shows only the negative tailstall locus because the positive locus is outside of the diagram”should be removed.“degespectively” should be “deg respectively”“Appendix A..” should be “Appendix A.”page 220, Eqn (4.81)change Vmc( N +DN)2 T1 D1rCnδrSbδrmax= to Vmc=( N N )− 2 T +D1 D1rCnδrSbδrmaxpage 225, Eqn (4.86b) “ C ” should be “ C ”.Y ry rpage 225Line 20, “three of these” should be “four of these”page 226, Eq (4.90) ψ1should read ψ1page 227, Eqn (4.96) “ C ” should be “ C ”.page 227, Eqn (4.97)(4.103) “ Φ ” should be “ Φ 1 ”Y ry rpage 227, Line 6page 228, Eqn (4.98)The first sentence should be removedVariables a 11 , b 11 , and c 11 should be a, b, and cErrata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 2001 5

page 228, Eqn (4.99)page 228, Eq (4.100)Variables a 11 , b 11 , and c 11 should be a, b, and cδa 1should read δr 1, Variables a 11 , b 11 , and c 11 should be a, b, and cpage 228, Eqn (4.102) “ Φ ” should be “ Φ 1 ”page 228, Eqn (4.102a) Variable a 11 should be a.page 228, Eqn (4.102b) Variable b 11 should be b.page 228, Eqn (4.102c) Variable c 11 should be c.page 232, Eqn (4.113b) “ γ 1 ” should be “ Θ 1 ”page 232, Eqn (4.114a) “ γ 1 ” should be “ Θ 1 ”page 233page 235Third paragraph, 2 nd line. The word “forward” should be changedto “aft”Last line, “for a conventional airplane” should be “for a canardairplane”page 237 Line 7, “in Eqn (4.10)” should be “in Eqn (4.131)”page 237, Lines 10-11Should read: “From Eqn (4.133) it may be concluded that as longas L h is positive (i.e. ‘up’) and ( x − x ) is positive the canardacwfload to trim, L c , will also be positive (i.e. ‘up’).cgpage 242, Eqn (4.136) change HM = ChqSeceto HM = ChqhSecepage 244, Section 4.5.1page 253page 255q qLast paragraph, change h h = to hhh =qhqLast paragraph, 1 st line, “found by by” should be “found by”Last paragraph, 2 nd line, “from Eqn 4.169)” should be “fromEqn (4.169)”page 256,3 rd line above Fig 4.34 ‘stick-force-per-‘g’’ should be just ‘stick-force’.οοpage 259, Figure 4.36 In graph a) “ δ = 2 ” should be “ δ = 2 ”et epage 263, Line 2Second “the” should be removed.Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 2001 6

page 267 Definitions for each variable should be: C , C , Cnegative, negative, positive respectivelyhδ hr δ hr βt vnormallypage 267, Eqn (4.192)page 268Ch βshould be Ch rβv∂βInclude in τrdefinition: τr= and is normally negative∂ δrpage 269 Eqn (4.203)∂FG h qScCr= −∂βCr v 1 r r hδrnδrreplaces:Cnβfree∂FG h qScCr=∂βCr v 1 r r hδrnδrCnβfreepage 273, Line 4“and (4.209)” should be removed.page 278, Line 6 HM should refer to Eqn (4.136).page 278, Eqn (4.225)page 278, Line 22Equation # 4.225 is repeated for two different equations.Should read, “The hingemoment coefficient equation…”∂δpage 280, Line 15 “e∂n∂F” should be “s∂ n”page 281 List at end of page is inconsistent with Figure 4.49page 288, Line 2page 288, Line 14page 288-290page 291page 291, Eqn.(4.250)Sentence should read “Exceptions to this are airplanes like theB-52.”Remove “!” after “nose-gear.”“ground” subscript should be “g”Last paragraph, 1 st line. The word “are” should be “area” θ should be θmgErrata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 2001 7

page 292, Figure 4.52bx labels should be reversed for x = 38 ft and x = 39 ftcg gcg gcg gpage 307, Eqn (5.1a)CInsert θ after mg . Remove DU .1⎧uumu=− mgqcosq1+ q1S ⎨− ( CD + 2C 1) ( 2u D + CT + Cx Tx) +Uu 1⎩1 U1( CD CL 1) α CD δαδ e}− − −epage 307, Eqn (5.1b) Insert θ after mg .⎧u( 1 ) sin 1 1 ⎨ ( L 2 L ) ( L D )m w − U q =− mgq q + q S − C + C − C + C α +u 1 α 1⎩U1 αcqcC C C⎫δ− L − L − αq Lδe⎬ 2U1 2Ue1 ⎭page 307, Eqn (5.1c)page 314, Figure 5.6page 316, Line 9page 318Should beuI q= q Sc C + C + C + C + C α + C α +u{( 2 ) ( 2 )yy 1 m m m m m mU1 U1u 1 TuT1α Tα αcqcC C C⎫δ+ m + m + αq mδe⎬ 2U1 2Ue1 ⎭Solid black line needs removed.Line is “the system is zero” should be “the system are zero”First line of second paragraph, change θ to θpage 319 Table 5.1, third last equation, change CmαtoCmαδ { α α α δeα}{ }B =− X U − Z M + Z + M U + Z + Z Xpage 322, Eqn (5.35) change u e( 1 ) q ( 1 q)to u =− ( 1− ) q + + ( 1+ q)+B X U Z M Z M U Z Z Xδeα α α δeαpage 324, Line 16Remove the list number “1)” and align row to far left.page 328, Eqn (5.48) “>” should be “” should be “

page 333, Eq (5.54)the equation should have a minus “ - “ before ζ 3,4 ω n3,4 and ζ ph ω nphpage 333, Line 8 T 1 = − 0.35 and T 2 = 0.28page 333, Eq (5.56)page 338 Equation (5.69),the equation should have a minus “ - “ before ζ 3,4 ω n3,4 and ζ 3rd ω n3rdθ () s= −δe()s( Zδ s− XuZδ + XδZu)e e e⎛ 2 gZu⎞U1⎜s −Xus−⎟⎝ U1⎠page 340 3 rd line. The word “ration” should be “ratio”page 340Equation (5.76), the term Zδ Me α should be − ZδMe αpage 340 Equations (5.76) to (5.78), change D 1 to D 1page 342, Eqn (5.82a)page 342, Eqn (5.82b)page 342, Eqn (5.82c)In equation, “ 2 ζpsω ” should be “ 2 ζpsnω ”spnpIn equation, “ 2 ζpsω ” should be “ 2 ζpsnω” and “ 2 ζα” should bespnωpnα“ 2 ζα s ”ωnαIn equation, “ 2 ζpsω ” should be “ 2 ζpsnω ”spnppage 350, Line 5 “ φ()/ s δ () s ” should be “ φ()/ s δ () s ”page 364, Line 28 Eqn (5.120) should be Eqn (5.121)page 371 Equations (5.136) to (5.138), change D 2 to D 2epage 381, Figure 5.24page 381, Figure 5.25page 396, Line 25For Damping Ratio “-1/T” should be “1/T”For Damping Ratio “-1/T” should be “1/T”Should read, “…say 10 deg/deg/sec, a 3 deg/s pitch rate…”Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 2001 9

page 398, Line 2page 401, Figure 5.44“elevator deflection” should be “rudder deflection”On the Y B vector, the smaller vector should be labeled “q”page 405, Lines24-28 Omit paragraph contained by lines 24-28.page 407, Line 13 cosθ = 1 for small angles.page 424, Table 6.4The Civilian Requirements FAR-23 are updated to the following:For wheel controllers:∂F s ( W 100)20.0> TOand∂n nlimit−1 nlimit−150.0but not more than:nlimit−1For stick controllers:∂FsW 15.0> and∂n140 n −1limit35.0but not more than:nlimit−1page 427, Line 6page 427, Line 7Remove the return so “be” and “written” are on the same line.“time to double” should be “time-to-double.”page 434, Line 12 Reference 6.5 should be Reference 6.6.page 460, Lines 21-22page 461, Lines 20-23page 466, Lines 26-27page 466, Lines29-31Appendix BReference should be: Roskam, J.; Airplane Design, Parts Ithrough VIII; Design, Analysis, and Research Corporation, 1440Wakarusa Drive Suite #500, Lawrence, KS 66049, USA; 1990Address should be: 1440 Wakarusa Drive Suite #500, Lawrence,KS 66049, USA Tel. 785-832-0434 Fax: 785-832-0524Lines should read “ Design, Analysis, and Research Corporation,1440 Wakarusa Drive Suite #500, Lawrence, KS 66049, USA”Lines should read “Design, Analysis and Research Corporation,1440 Wakarusa Drive, Suite #500, Lawrence, KS 66049, USA Tel.785-832-0434 Fax: 785-832-0524Ch βshould be Ch rβvfor all examples.Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 2001 10

page 487, B2page 560, Lines18-19C.G. location should be 0.33 cReference should be: Roskam, J.; Airplane Design, Parts Ithrough VIII; Design, Analysis, and Research Corporation, 1440Wakarusa Drive Suite #500, Lawrence, KS 66049, USA; 1990Errata: Airplane Flight Dynamics and Automatic Flight Controls Part I, Year of Print: 2001 11