DESIGN, ANALYSIS AND RESEARCH CORPORATION ERRATA: AIRPLANE DESIGN PART I Copyright 1985-89 by Dr. Jan Roskam Year of ...
450 downloads
2745 Views
88MB Size
Report
This content was uploaded by our users and we assume good faith they have the permission to share this book. If you own the copyright to this book and it is wrongfully on our website, we offer a simple DMCA procedure to remove your content from our site. Start by pressing the button below!
Report copyright / DMCA form
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 = WPL + WCREW + Wpexp
1
6
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 LTO by C L max max
TO
page 106, line 2
replace four factors: with five factors:
page 115, Eqn. (3.18)
VA =1.1Vs
PA
page 132, 4th line
delete “an”
page 150, Eqn. (3.32)
RCh = RC0 1 − h / habs
page 152, Eqn. (3.38)
−1 L 2 T −2 T 2 sinγ = P − Pdl − Pdl + 1 + W dl D W
1
Errata: Airplane Design Part I, Year of Print: 1985, 1989
6
1
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.
> 0 = :25,000?
VA = 21,200 1.3 /1.2 VA
2
1/2
5C
2 1/2
= 158 kts should be
= 158 kts
Errata: Airplane Design Part I, Year of Print: 1985, 1989
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 K Λ 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 Swf 0.3 0.6 0.3 0.6 S ∆Cl max 0.58 0.29 2.32 1.16 Z fh Zfh should be . c 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).
Errata: Airplane Design Part II, Year of Print: 1985, 1989
1
Section 7.2.2 Jet Transport The results of step 7.4 should be: Take-off flaps Landing flaps Swf 0.6 0.8 0.6 0.8 S ∆Cl max 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 Swf 0.4 0.8 1.0 S ∆Cl max 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 D = 0 .75 N tcrit should be N D = 0 .25 N tcrit
Eqn (11.14)
N D = 0 .25 N tcrit should be N D = 0 .10 N tcrit
2
Errata: Airplane Design Part II, Year of Print: 1985, 1989
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 III, 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 IV, Year of Print: 1986, 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)
nlim pos ≥ 2.1 + 24,000 / 0GW + 10,0005
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 by Λ 1/4 V
page 72 - 74
All comments about the canard weight should reference 5.2.1.1.
page 74 Eqn (5.19)
Replace 1 / 2 H by Λ 1/2 H
Eqn (5.20)
(
Wv = K v Sv 3.81 Sv0.2VD
) (1000
Replace 1 / 2 V by Λ 1/2 V page 75, Eqn (5.23)
1 6 1 6 3 8 0.692
0.374
)
cos Λ c 2 − 0.287 v
0.590
Wf = 0.04682 WTO Pmax l f −n 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)
lh = distance from wing root c/4 to horizontal tail root c/4 in ft
page 78, Eqn (5.29)
Wn = K nWTO should be Wn = K n PTO
Errata: Airplane Design Part V, Year of Print: 1985, 1989
1
page 79 2nd line
Eliminate and replace by “PTO = Take-off power in HP”
Eqn (5.32)
Wn = 0.045(PTO )5 / 4 (N e )−1 / 4
page 81 Wg = 0.013WTO + 0.362 (WL )
0.417
Eqn (5.38)
( nult .l )0.950 (lsm )
0.183
+ 0.0013WTO + 0.007157 (WL )
0.749
(nult .l ) (lsn )
0.788
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)
Wai + Wp = 1.03(N e )0.3 (PTO )0.7
page 90, Eqn (6.14)
page 92, Eqn (6.23)
+ 6.2 +
Method assumes that the number of engines equals the number of propellers Wf W fs = 1.6 K fsp
0.727
See the associated insert for the comparison of Torenbeek and GD methods. page 93,
page 95, Eqn (6.34b)
Add an increment of 5 to all equation numbers throughout Chapter 6 (i.e., Eqn. (6.22) becomes Eqn. (6.27)). Wapsi = 0.4K b (N e )0.2 (PTO )0.8
page 98,
Add an increment of 1 to all equation numbers throughout Chapter 7.
page 99, Eqn (7.4)
Wfc = 0.33 WTO
page 108,
Eqn (7.44) Remove the ( before N pax 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.
2
1 6
2/3
Errata: Airplane Design Part V, Year of Print: 1985, 1989
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
xac = xac / c
page 27, Eqn (4.9)
S S CL = CL − CL c − CL h w c S h S
h
h
= 2α
S 2 b fus
page 46, Eqn (4.33)
C DL
page 47, Figure 4.20
M c = M sin α
fus
page 49 Eqn (4.39)
CDL
Eqn. (4.41)
CDo
S
4
+ η cdc α
= α 2 Sb fus / S
fus
= C f fus
S plf fus S
9
fus
3
Swet fus
S fus
+ CD N
+ CD A + CD + CDb A0 NC 5 fus 2
S fus S
Sb fus S plf fus 3 = F 2α 2 + cdc α fus S S
page 52, Eqn (4.43)
C DL
page 70, 9th line
Should read
page 73 Eqn. (4.60)
Add:
Last line
Should read: Chapter 8.
page 77, Eqn. (4.63)
∆cl2 = +0.056 in 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)
∆C Dtrim
“... of 4.2.2.1 but with the appropriate...”
εn > 0 for upwash and εn < 0 for downwash
16
prof
(
= ∆C D p
(
)
Sef cos Λ c 4 h S Λc 4 = 0 h h
)
Sh S
Scf + ∆C D p cos Λ c 4 c S Λc 4 = 0 c c Errata: Airplane Design Part VI, Year of Print: 1987, 1990
Sc S 1
page 142
The reference to Chapter 6 in Part IV should be Chapter 7
page 171, Eqn. (6.25)
Replace
page 177, 22nd line
Section on supersonic jet inlets should be Section 6.2.3.4
•
•
page 181, Eqn. (6.44)
PJDV with PD • Where PD follows from Eqn. (6.19)
Finl
%K (K µ − 1 1 ) = 1 + 1.75 & KK µ AA − 1 KK ' * inl
m
inl
c
( f1 ){(c + c1 ) / c} + η 2 clδ f2 (δ f2 )(c ′ / c)
page 229, Eqn. (8.7)
∆cl = η1 clδf δ 1
page 233, Eqn. (8.10)
y −y Φ TEUPPER = arctan{ 10 90 100 } c
page 245, Eqn. (8.20)
α w = α + iw
page 268, Eqn. (8.32)
Should be C Lo = C Lo
wf
6
1
+ C Lα η h Sh S −ε oh − α o L h h
1
6
+ C Lα η c S c S ε oc − α o L c c
where: α o L and α o L can be found using the method of Section h c 8.1.3.1. page 269, Eqn (8.37)
For jet airplanes, the horizontal tail dynamic pressure should be calculated from: π zhwake 2.42 CDo cos 2 2 ∆z wake w = − 1 ηh xhwake + 0.30 c where:
C Do is the wing zero-lift drag coefficient as found from 4.2.1.1. w
zhwake = a sin (γ h − α − iw + ε h )
xhwake = a cos (γ h − α − iw + ε h ) xhwake
∆zwake = 0.68c C Do w
2
c
+ 0.15
Errata: Airplane Design Part VI, Year of Print: 1987, 1990
page 269, Eqn (8.37) (Cont.) with:
a and γ h shown in Figure 8.63; c as the wing mean geometric chord;
α as the airplane angle of attack; iw as the wing incidence angle; and 1.62C Lw
ε cl = page 270, Figure 8.63
πA
Should be H orizo ntal Tail A ero dy n am ic C enter
Z hwake
∆Z wake
a
ZTE
W ing R o o t C ho rd
γh
iw
C en terline of W ak e and Vortex S h eet
εh W ak e L im its
P aralle l to the B o dy A x is (R efe rence A x is)
α X hwake F ree S tream
l
page 275, Eqn. (8.50)
Parenthesis after ε0h should be moved to after dε/dα.
∆ε Ab b should be degrees f
page 279, Fig. (8.70)
Units for
f
∆CL
w
page 280, Eqn. (8.54)
∆C Lmax = K cw ∆C Lmax
1
6
w
− C Lα ∆α w c w δ
1
6
3
+ S c S ∆C Lmax + S h S C Lα − ∆ε f c h
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 ref − 0.25 ∆C Lw
3
8
where: ∆C Lw is the wing lift increment due to flaps. page 320, Eqn (8.78)
Replace ‘iw ’ with ‘−iw ’.
Errata: Airplane Design Part VI, Year of Print: 1987, 1990
3
page 323, 1st line
Should read
page 333, Eqn. (8.97)
ε = ε oh + α
page 333, Eqn. (8.97)
page 340, Eqn. (8.107)
airplane zero angle of attack. . .
dε h dα dε ε = ε oc + α c dα K Ti =
550 SHPAVi ρ
(2W S)
32
DPi 2
page 342, Eqn. (8.108)
1dC N dα 6 P 4dε Pi dα 94l Pi 910.7964 DPi 92 "# i 1dCm dC L 6 N = ∑ ## ScC Lα i =1 w ! $
page 374, Eqn. (10.8)
CT
page 375, Last Line
∂C D ∂Cm should be∂C D ∂M .
page 377 Eqn. (10.12)
Cmu = −CL1 ∂Xaca / ∂M M
Eqn. (10.13)
CTx
Eqn. (10.15)
CTX = ( M1 / qS )(∂Treqd / ∂M ) − 3CTX
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)
z h should be ‘the vertical distance between the horizontal tail aerodynamic center to the fuselage center line’.
n
page 397, 6th line from bottom
X 1
= CD
1
4
u
9
0 53
8
= 1 qS ∂Preqd ∂u − 3CTx 1
u
1
Replace C yβ by C yβ
v
page 398, Eqn (10.44)
i=n CnT = − Sum β i =1
page 401~415, Fig.30~33
z v = z p cos α f − l p cos α f
4
%&1dCN dα 6 00.7954 DP 92 4l p 9() Sb"# pi i i * !' $ Errata: Airplane Design Part VI, Year of Print: 1987, 1990
page 417, Eqn (10.50)
Cy = 2Cy
v
βv
p
z cos α − l sin α − z + 3 sin Γ1 − 4z sin Γ 4C 9 b b v
v
lp
Γ =0 CL = 0
where: z - is the vertical distance between the cg and the wing root quarter-chord point.
4C 9 lp
page 418, Figure 10.35
page 419, Eqn. (10.55)
Γ=0 CL=0
Replace
4C 9 4C 9
lp Γ
lp
page 421, Eqn.(10.62) Cn p
w
=
%K &K4Cn p '
=k β
Γ =0
βClp k
βC k lp
with
CL= 0
βC k lp
CL=0
4z z = 1 − w sin Γ + 12 w sin Γ b b
(K )K 4 M * = ∆c / 4c δ 9
9 !
9
2
C L C = 0 C L w + Cn p ε t ε t + ∆Cn p L
page 422, Eqn. (10.66)
αδ f
page 424, Eqn. (10.71)
(C )
page 435, Eqn. (10.89)
C Di
lα
l
f
x = 0.5 + 2 w Lqw c M =0
h
α δ f δ f "#α δ f δ f $
=
S 2C L C Lα η h h h πAe S
=
S 2C L C Lα η c c c πAe S
C Lα w
page 439, Eqn. (10.97)
C Di
Eqn. (10.100)
Cmi
page 440, Eqn (10.102)
Replace clα with clα h c
page 446, Eqn (10.110)
clδ =
c
c
= C Lα η c Vc c
4clδ 9theory 4 lδ 9theory clδ
c
k'
where k' is found from Figure 8.13
Errata: Airplane Design Part VI, Year of Print: 1987, 1990
5
page 447, Eqns. (10.111) & (10.113)
It is assumed that:
page 461, Eqn. (10.123)
Should read:
C lδ
Sv C yδ = Kδ C Lα v S r
left
= Cl
δ right
%K cl (K k' %K2α δ 7CL (K δ &K c )4c 9 & ) 4' lδ 9theory K* lδ theory clα v K' 2α δ 7cl K*
Eqn (10.123) is correct for a single vertical tail only. For a twin vertical tail:
C yδ
Cyβ v wfh = 2 Cyβ v eff 0
r
5
Kb CLα v
C β where: C β y
v0wfh5
y
veff
Sv S
%K cl (K k' %K 2α δ 7CL (K δ &K c )4c 9 & ) 4' lδ 9theory K* lδ theory clα v K' 2α δ 7cl K*
is found from Figure 10.17.
All other parameters are the same.
page 467, Eqn. (10.129)
4chα 9theory is found from Figure 10.63b. The parameter clα
4 9theory
in Figure 10.63b is itself found from Figure 10.64a
clα
with the assumption that tan page 470, 1st line Eqn. (10.130)
Φ ' TE t = . c 2
(10.126) should be (10.128). clα is obtained from Figure 10.64a with the assumption clα
4 9theory
that tan
Φ ' TE t = . c 2
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
6
Errata: Airplane Design Part VI, Year of Print: 1987, 1990
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.
page 39, Figure 2.5 page 44, Eqn. (2.39)
Sh =
Typical numerical values for gearing ratios are given in Table 4.1 of Part IV, not Part VI. z T should be negative as shown Should read:
− z T T + z D D + W 3 x mg − x cg + µ g z mg 8 − L wf 4 x mg − x acwf + µ g z mg 9 − C mac q rot Sc + I yymg Θ wf
g
q rot 4 x mg − x ach + µ g z mg 9C Lh max
page 49, Eqn. (2.54)
The 4th term on the left hand side should read: ‘+ Yng xng + x cg - ...’
page 50, Eqn. (2.57)
The 4th term on the left hand side should read: 0.025 Ψ A + Ψsteer Png x ng + x cg
page 98, 1st sentence
Should read, “Civil: FAR 23.201, 23.203, 23.205, ...”
page 152, Eqn. (5.59)
T sin α + φ t + CL qS − W cos φ − W / g U1Q1 sin φ = 0
page 159, Last sentence of 1st para.
Should read, “See Section 5.3.”
page 161, Eqn. (5.77)
RD =
page 164, AS-5263
thrust required for level flight at 1.15Vs , not 1.15Vs
3
8
1
1
6 3
8
0
6
J0W / S502 / ρ53C
Errata: Airplane Design Part VII, Year of Print: 1988, 1991
2 D
80
/ CL3 cos γ
5
5L
3 1/ 2
. PA
1
