Airplane Design Vol 1-7, Errata

Errata: Airplane Design Part I, Year of Print: 1985, 1989 1 DESIGN, ANALYSIS AND RESEARCH CORPORATION ERRATA: AIRPLANE DESIGN PART I Copyright  1985-89 by Dr. Jan Roskam Year of Print, 1985, 1989 (Revised June 11, 1997) page 51, Eqn. (2.9) units for cP= (lbs/hr)/hp line 6 from bottom replace 1,000 nm with 1,000 sm page 52, line 3 1000 is standard miles page 61, Table 2.19 Take-off and Landing: groundrun of less than 2,400 ft. page 64, line 3 and 5 W is the take-off weight: WTO page 69, Eqn. (2.23) D W W WPL CREW p= + +1 6 exp Where Wpexp is the weight of the expended payload. (i.e., Missles, bombs, etc.) page 95, line 14 from bottom remove “range of” page 98, line 8 from bottom replace C CLTO L TOmax max by page 106, line 2 replace four factors: with five factors: page 115, Eqn. (3.18) V VA sPA =1 1. page 132, 4th line delete “an” page 150, Eqn. (3.32) RC RC h hh abs= −0 1 /1 6 page 152, Eqn. (3.38) sin = T W P Pdl dlγ − − +               − − 2 2 1 2 1P + L D T Wdl 2 Errata: Airplane Design Part I, Year of Print: 1985, 1989 page 186, Section 3.7.4.2 line 3 ...groundrun as < 2,400 ft. line 7 SL = 1.9 x 2,400 = = 4,500 ft. From Figure 3.16 SL = 4,500/0.6 = 7,500 ft. From Figure 3.17 this yields: VA2 = 25,000 kts2. V ktsA = =21 200 1 3 1 2 158 2 1 2 , . / . / 0 5> C should be V ktsA = =25 000 158 1 2 , /: ? Errata: Airplane Design Part II, Year of Print: 1985, 1989 1 DESIGN, ANALYSIS AND RESEARCH CORPORATION ERRATA: AIRPLANE DESIGN PART II Copyright  1985-89 by Dr. Jan Roskam Year of Print, 1985, 1989 (Revised June 11, 1997) page 102, Step 3.1, 2nd line ...falls into one of the eight catagories... page 158, Step 6.10 Eqn. (6.1) should be Eqn. (6.2) page 170, Eqn (7.8) and (7.11-18) Cl should be cl pages 176 to 185 The example problems of Section 7.2 are incorrect. The KΛ factor was multiplied instead of divided to yield the Clmax values for Step 7.4 of 7.2.1, 7.2.2, and 7.2.3. Each example will be addressed below. Section 7.2.1 Twin Engine Propeller Driven Airplane The results of step 7.4 should be: Take-off flaps Landing flaps S S wf 0.3 0.6 0.3 0.6 ∆Clmax 0.58 0.29 2.32 1.16 Zfh should be Z c fh . For Step 7.5, the referenced equations and figures are wrong: Eqn. (7.15) should be Eqn. (7.16). Eqn. (7.14) should be Eqn. (7.15). Eqn. (7.13) should be Eqn. (7.14). Figure 7.7 should be Figure 7.8. Figure 7.3b should be Figure 7.4. Eqn. (7.10) should be Eqn. (7.11). 2 Errata: Airplane Design Part II, Year of Print: 1985, 1989 Section 7.2.2 Jet Transport The results of step 7.4 should be: Take-off flaps Landing flaps S S wf 0.6 0.8 0.6 0.8 ∆Clmax 3.00 2.24 3.84 2.88 For Step 7.5, the referenced equations and figures are wrong: Eqn. (7.10) should be Eqn. (7.11) Figure 7.3b should be Figure 7.4 Section 7.2.3 Fighter The results of Step 7.4 should be: Take-off flaps S S wf 0.4 0.8 1.0 ∆Clmax 4.00 2.000 1.60 These corrections will affect the results of each sample problem. It is left to the reader to complete the sample problems using the correct results of Step 7.4. The summary and referenced drawings of Step 7.6 may change due to these corrections. pages 178, 181, and 184 Under Step 7.4, K∆ should be KΛ page 267 Eqn (11.13) N ND t crit = 0 75. should be N ND t crit = 0 25. Eqn (11.14) N ND t crit = 0 25. should be N ND t crit = 0 10. Errata: Airplane Design Part III, Year of Print: 1986, 1989 1 DESIGN, ANALYSIS AND RESEARCH CORPORATION ERRATA: AIRPLANE DESIGN PART III Copyright 1986-89 by Dr. Jan Roskam Year of Print, 1986, 1989 (Revised March 15, 1999) page 15, Table 2.3 Switch values for β1 and β2 page 194, 8th line from top replace “stability” with “Stability”. Errata: Airplane Design Part IV, Year of Print: 1986, 1989 1 DESIGN, ANALYSIS AND RESEARCH CORPORATION ERRATA: AIRPLANE DESIGN PART IV Copyright  1986-89 by Dr. Jan Roskam Year of Print, 1986, 1989 (Revised December 14, 1999) page 54, Table 2.18 For fighters and trainers, the details are in Figure 2.26, not Figure 2.25. page 380, 7th line from top replace “is” with “are” Errata: Airplane Design Part V, Year of Print: 1985, 1989 1 DESIGN, ANALYSIS AND RESEARCH CORPORATION ERRATA: AIRPLANE DESIGN PART V Copyright  1985-89 by Dr. Jan Roskam Year of Print: 1985, 1989 (Revised December 14, 1999) page 34, Eqn (4.13) n GWposlim . , / ,≥ + +2 1 24 000 10 0000 5 page 43, 12th line from top VA should be 217 kts. page 45, 8th line Change Selene to Eris page 61, under Step 6 nult = 7.33 should read nlim = 7.33 page 71 Eqn (5.12) 57.5 should be 174.04 Eqn (5.13) 15.6 should be 639.95 Replace exponent 1.249 with 0.1249 page 72 6th line replace ‘ib’ with ‘in’ 13th line replace 1 4/ V 1/4Vby Λ page 72 - 74 All comments about the canard weight should reference 5.2.1.1. page 74 Eqn (5.19) Replace 1 2/ H 1/2Hby Λ Eqn (5.20) ( ) ( )0.2 23.81 1000 cos 0.287v v v v D c vW K S S V = Λ −   Replace 1 2/ V 1/2Vby Λ page 75, Eqn (5.23) W W P lf TO f n= −0 04682 0 0 374 0 590 . .692 max . . 1 6 1 6 3 8 where Pmax is the maximum fuselage perimeter expressed in feet. page 76 Eqn (5.24) Npax is the number of passengers including the pilot. Eqn (5.26) Replace 2 x 10.43 by 10.43 page 77, Eqn (5.27) hl = distance from wing root c/4 to horizontal tail root c/4 in ft page 78, Eqn (5.29) W K Wn n TO= should be W K Pn n TO= 2 Errata: Airplane Design Part V, Year of Print: 1985, 1989 page 79 2nd line Eliminate and replace by “PTO = Take-off power in HP” Eqn (5.32) ( ) ( ) 4/1e4/5TOn NP045.0 W −= page 81 Eqn (5.38) ( ) ( ) ( ) ( ) ( )( ) 0.1830.417 0.950 . 0.7880.749 . 0.013 0.362 6.2 0.0013 0.007157 g TO L ult l sm TO L ult l sn W W W n l W W n l = + + + + + 7th line from bottom Replace Nult.l by nult.l 4th line from bottom Replace 62.61 by 62.21 page 85 Section 6.1.2, 9th line Should read: Equations (6.4) and (6.6) may also be used... page 87, Eqn (6.8) ( ) ( ) 7.0TO3.0e pai PN1.03 W W =+ page 90, Eqn (6.14) Method assumes that the number of engines equals the number of propellers page 92, Eqn (6.23) W W Kfs f fsp =       16 0 727 . . See the associated insert for the comparison of Torenbeek and GD methods. page 93, Add an increment of 5 to all equation numbers throughout Chapter 6 (i.e., Eqn. (6.22) becomes Eqn. (6.27)). page 95, Eqn (6.34b) ( ) ( ) 8.0TO2.0ebapsi PN0.4K W = page 98, Add an increment of 1 to all equation numbers throughout Chapter 7. page 99, Eqn (7.4) W Wfc TO= 0 33 2 3. /1 6 page 108, Eqn (7.44) Remove the ( before Npax in the cabin windows weight component. page 109, Eqn (7.46) Kst = 0 for no ejection seat page 111, 3rd line of Section 7.12 Should read: Part IV, Chapter 3. Errata: Airplane Design Part VI, Year of Print: 1987, 1990 1 DESIGN, ANALYSIS AND RESEARCH CORPORATION ERRATA: AIRPLANE DESIGN PART VI Copyright  1987-90 by Dr. Jan Roskam Year of Print, 1987, 1990 (Revised December 14, 1999) page xx x x cach ach = / page 27, Eqn (4.9) CLw CL CLc Sc S CLh Sh S = − − page 46, Eqn (4.33) 322 b plffus fusD dL cfus S S C c S S α η α= + page 47, Figure 4.20 sincM M α= page 49 Eqn (4.39) C S SDL fus bfus= α 24 9 / Eqn. (4.41) C C S S C C C C S SDo fus f fus wet fus fus DN DA DA NC Db fus fus = � � � � � � + + + + � � � � � �2 0 5 page 52, Eqn (4.43) 322 b plffus fusD dL cfus S S C F c S S α α    = +    page 70, 9th line Should read “... of 4.2.2.1 but with the appropriate...” page 73 Eqn. (4.60) Add: εn > 0 for upwash and εn < 0 for downwash Last line Should read: Chapter 8. page 77, Eqn. (4.63) ∆c il n2 0 056= + . 1 6 with in expressed in degrees page 86 3rd line Should read: ... from Eqn. (4.6) Eqn. (4.74) ‘Chapter 9’ should be ‘Chapter 8’ page 105, Eqn (4.84) ( ) ( ) 404 404 cos cos ef h D D ctrim p hprof c hh cf c D cp c c cc S SC C S S S SC S S Λ = Λ =   ∆ = ∆ Λ         + ∆ Λ      2 Errata: Airplane Design Part VI, Year of Print: 1987, 1990 page 142 The reference to Chapter 6 in Part IV should be Chapter 7 page 171, Eqn. (6.25) Replace P JDV • with P D • Where P D • follows from Eqn. (6.19) page 177, 22nd line Section on supersonic jet inlets should be Section 6.2.3.4 page 181, Eqn. (6.44) F A A inl inl inl m c = + − � �� � �� − � � � � � � � � � � % & KK ’ KK ( ) KK * KK 1 1 75 1 1 1 . µ µ page 229, Eqn. (8.7) ( ) ( ){ } ( )( )∆c c c c c c c cl l f f l f f=   + +   ′η δ η δδ δ1 1 1 1 2 2 2/ / page 233, Eqn. (8.10) Φ TEUPPER y y c = − arctan{ }10 90 100 page 245, Eqn. (8.20) α αw wi= + page 268, Eqn. (8.32) Should be C C C S S C S S Lo Lowf L h h h oh oLh L c c c oc oLc = + − −�� � � + −�� � � α α η ε α η ε α 1 6 1 6 where: α oLh and α oLc can be found using the method of Section 8.1.3.1. page 269, Eqn (8.37) For jet airplanes, the horizontal tail dynamic pressure should be calculated from: 22.42 cos 2 0.30 1 h hwake Dow wake h wake C z x c zpi η ∆      + = − where: Dow C is the wing zero-lift drag coefficient as found from 4.2.1.1. ( )sinh h w hwakez a iα εγ= − − + ( )cosh h w hwakex a iα εγ= − − + 0.150.68 hwakewake Dow x C c z c   +   ∆ = Errata: Airplane Design Part VI, Year of Print: 1987, 1990 3 page 269, Eqn (8.37) (Cont.) with: a and hγ shown in Figure 8.63; c as the wing mean geometric chord; α as the airplane angle of attack; wi as the wing incidence angle; and 1.62 Lw cl C A ε pi = page 270, Figure 8.63 Should be W a k e L im its H o riz o n ta l Ta il A e ro d y n a m ic C e n te r C e n te rl in e o f W a k e a n d Vo r te x S h e e t P a ra l le l to th e B o d y A x is (R e fe re n c e A x is ) F re e S tr e a m W in g R o o t C h o rd l a wi α TEZ hwakeZ wakeZ∆ hε hwakeX hγ page 275, Eqn. (8.50) Parenthesis after ε0h should be moved to after dε/dα. page 279, Fig. (8.70) Units for ∆ε ∆ f f L w Ab b C � �� � �� should be degrees page 280, Eqn. (8.54) ∆ ∆ ∆ ∆ ∆ C K C C S S C S S C Lmax cw Lmaxw L w w c c Lmaxc h L h f = − � � � � + + − α δ α α ε 1 6 1 6 3 8 page 305, Eqn (8.73) The bar over the 2 should be over the c. page 311, Eqn (8.74) The first term on the r.h.s. should read: x Cref Lw− 0 25.3 8∆ where: ∆CLw is the wing lift increment due to flaps. page 320, Eqn (8.78) Replace ‘i w ’ with ‘−i w ’. 4 Errata: Airplane Design Part VI, Year of Print: 1987, 1990 page 323, 1st line Should read airplane zero angle of attack. . . page 333, Eqn. (8.97) ε ε α ε α = + �� � �oh hd d page 333, Eqn. (8.97) ε ε α ε α = + �� � �oc cd d page 340, Eqn. (8.107) ( )K SHP W S D Ti AVi Pi = 550 2 3 2 2 ρ page 342, Eqn. (8.108) dC dC dC d d d l D ScCm L N N Pi Pi Pi Pi L wi n 1 6 1 6 4 94 91 64 9 = � ! " $ # # #= ∑ α ε α α 0 79 2 1 . page 374, Eqn. (10.8) C CTX D1 1 = page 375, Last Line ∂ ∂C CD m should be∂ ∂C MD . page 377 Eqn. (10.12) C C X M Mmu L aca= − 1 ∂ ∂/4 9 Eqn. (10.13) C qS P u CTxu reqd Tx= ∂ ∂ −1 3 10 53 8 Eqn. (10.15) C M qS T M CTXu reqd TX= −( / )( / )1 13∂ ∂ page 382, Eqn (10.24) Add a ‘)’ to the end of Equation 10.24 2nd line below Eqn (10.24) Equation ‘(10.23)’ should be equation ‘(10.22)’. page 390, Fig. (10.16) hz should be ‘the vertical distance between the horizontal tail aerodynamic center to the fuselage center line’. page 397, 6th line from bottom Replace C Cy y vβ β by page 398, Eqn (10.44) C i n Sum i dC d D l SbnT N pi Pi piβ α= − = = %&’ ()* � ! " $#1 0 79 2 1 6 0 54 9 4 9. page 401~415, Fig.30~33 fpfpv lzz αα coscos −= Errata: Airplane Design Part VI, Year of Print: 1987, 1990 5 page 417, Eqn (10.50) C C z l z b z b Cyp y v v v v lp CL = − −� � � � + − � � � � = = 2 3 1 4 0 0 β α αcos sin sin sinΓ Γ Γ 4 9 where: z - is the vertical distance between the cg and the wing root quarter-chord point. C k C klp CL lp CL 4 9 Γ= = = = � �� � ��0 0 0 β β page 418, Figure 10.35 Replace βC k lp with βC k lp CL � �� � �� =0 page 419, Eqn. (10.55) C C z b z b lp lp w w 4 9 4 9 Γ Γ Γ Γ = = − + �� � � 0 2 1 4 12sin sin page 421, Eqn.(10.62) C C C C C Cn pw n p L CM Lw np t t np f f f fL= % &K ’K ( )K *K + + �� � � � ! " $#=4 9 4 90 ε ε α δ α δδ δ∆ page 422, Eqn. (10.66) α δδ αf l l fc c= ∆ / 4 9 page 424, Eqn. (10.71) ( ) 0 0.5 2 wL Lqw wM xC C c α=   = +   page 435, Eqn. (10.89) C C Ae C S SDih L L h h h = 2 pi η α page 439, Eqn. (10.97) C C Ae C S SDic L L c c c = 2 pi η α Eqn. (10.100) C C Vmic L c c c= α η page 440, Eqn (10.102) Replace l hcα with l ccα page 446, Eqn (10.110) c c c c kl l l theory l theoryδ δ δ δ= 4 9 4 9 ' where k' is found from Figure 8.13 6 Errata: Airplane Design Part VI, Year of Print: 1987, 1990 page 447, Eqns. (10.111) & (10.113) It is assumed that: C Cl left l rightδ δ � � � � = � � � � page 461, Eqn. (10.123) Should read: C K C S S c c c k c y r L v v l l theory l theory l v CL cl δ δ α δ δ δ α δ δ α α = % & K ’K ( ) K *K � � �� � � �� % &K ’K ( )K *K4 9 4 9 2 7 2 7 ' Eqn (10.123) is correct for a single vertical tail only. For a twin vertical tail: C C C K C S S c c c k c y r y v wfh y veff b L v v l l theory l theory l v CL cl δ β β α δ δ δ α δ δ α α = � � � �� � � � �� % & K ’K ( ) K *K � � �� � � �� % &K ’K ( )K *K 2 0 5 4 9 4 9 2 7 2 7 ' where: C C y v wfh y veff β β 0 5 � � � � � � � � � � is found from Figure 10.17. All other parameters are the same. page 467, Eqn. (10.129) ch theoryα4 9 is found from Figure 10.63b. The parameter c c l l theory α α4 9 in Figure 10.63b is itself found from Figure 10.64a with the assumption that tan 'Φ TE t c2 = . page 470, 1st line (10.126) should be (10.128). Eqn. (10.130) c c l l theory α α4 9 is obtained from Figure 10.64a with the assumption that tan 'Φ TE t c2 = . page 484, Eqn (10.145) Replace ‘αδ’ with ‘–αδ’. page 521, (Pratt and Whitney handbook errors) Pressure (psia) for 200,000 ft should be 0.002655 psia Pressure (psia) for 200,131 ft should be 0.002641 psia Pressure Ratio, δ, for 154,199 ft should be 0.001095 Errata: Airplane Design Part VII, Year of Print: 1988, 1991 1 DESIGN, ANALYSIS AND RESEARCH CORPORATION ERRATA: AIRPLANE DESIGN PART VII Copyright  1988-91 by Dr. Jan Roskam Year of Print: 1988, 1991 (Revised December 14, 1999) page 11, last sentence of 3rd para. Typical numerical values for gearing ratios are given in Table 4.1 of Part IV, not Part VI. page 39, Figure 2.5 zT should be negative as shown page 44, Eqn. (2.39) Should read: S z T z D W x x z L x x z C q Sc I q x x z C h T D mg cg g mg wf mg acwf g mg macwfg rot yymg rot mg ach g mg Lh = − + + − + − − + − + − + µ µ µ 3 8 4 9 4 9 �� max Θ page 49, Eqn. (2.54) The 4th term on the left hand side should read: ‘+ Y x xng ng cg+3 8 - ...’ page 50, Eqn. (2.57) The 4th term on the left hand side should read: 0 025. Ψ ΨA steer ng ng cgP x x+ +1 6 3 8 page 98, 1st sentence Should read, “Civil: FAR 23.201, 23.203, 23.205, ...” page 152, Eqn. (5.59) T C qS W W g U Qt Lsin cos / sinα φ φ φ+ + − − =1 6 0 5 1 1 0 page 159, Last sentence of 1st para. Should read, “See Section 5.3.” page 161, Eqn. (5.77) RD = W / S0 50 53 80 5J L2 2 3 3 1 2 / / cos / ρ γC CD L page 164, AS-5263 thrust required for level flight at 1 15. V s , not 1 15. V s PA .