Introduction to Flight 7th Edition Anderson Solutions Manual

Page 1

SOLUTIONS MANUAL TO ACCOMPANY

INTRODUCTION TO FLIGHT 7th Edition
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Chapter 2

ρ

/(1.2)(1.0110)/(287)(300) 1.41kg/m 1/1/1.410.71m/kg

One kg-mole, which has a mass of 4 kg, has 6.02 × 1026 atoms. Hence 1 kg has 26 26 1 (6.0210)1.50510 4 = ×× atoms. 20 26 6

= =´´=´

Totalinternalenergy(energyperatom)(numberofatoms) (1.03510)(1.50510)1.55810J -

2.3 3 2116 slug 0.00237 (1716)(46059)ft ρ == = + p RT 3 Volumeoftheroom(20)(15)(8)2400ft

Weight(5.688)(32.2)183lb == == ==

2116 slug 0.00274 (1716)(46010) ft

slug

3

consistent units,

(0.52)(1716)(530) ρ pRT==

PROPRIETARY MATERIAL. © 2012 The McGraw-Hill Companies, Inc. All rights reserved. No part of this Manual may be displayed, reproduced, or distributed in any form or by any means, without the prior written permission of the publisher, or used beyond the limited distribution to teachers and educators permitted by McGraw-Hill for their individual course preparation. A student using this manual is using it without permission.

2
ρ
2.1 5 2 3 = =pRT= v===
ρ ×
2.2 Mean kinetic energy of each atom 23 20 33 (1.3810)(500)1.03510J 22 =×× kT==
Total mass in the room(2400)(0.00237)5.688slug
p RT ρ == = -
2.4
3
0.002740.002370.00037 ft Δρ =-= 0.00037 %change(100)15.6%increase 0.00237 ρ ρ Δ ==´=
Since the volume of the room is the same, we can simply compare densities between the two problems.
In
3
Hence,
2
2.5 First, calculate the density from the known mass and volume, 3 m 15009001.67lbft ρ //==
1.67/32.20.052slugft.
ρ / == Also, T = 70 F = 70 + 460 = 530 R.
47,290lb/ft p = or 47,290/211622.3atm p ==

2.6 ρ p RT = npnpnRnT =++ 

Differentiating with respect to time, 111 ρ ρ =+ dpddT p dtdtTdt

or, T ρ ρ =+ dppdpdT dtdtdt

or, ρ ρ =+ dpddT RTR dtdtdt

At the instant there is 1000 lbm of air in the tank, the density is 3 m 1000/9001.11lb/ft

Also, in consistent units, is given that T = 50 + 460 = 510 R and that

From the given pumping rate, and the fact that the volume of the tank is 900 ft3, we also have

Thus, from equation (1) above,

3
PROPRIETARY MATERIAL. © 2012 The McGraw-Hill Companies, Inc. All rights reserved. No part of this Manual may be displayed, reproduced, or distributed in any form or by any means, without the prior written permission of the publisher, or used beyond the limited distribution to teachers and educators permitted by McGraw-Hill for their individual course preparation. A student using this manual is using it without permission.
(1)
ρ
== 3 1.11/32.20.0345slug/ft ρ ==
1/min1/min0.016/sec
dT
dt
===
FRR
3 m m 3 0.5lb/sec 0.000556lb/(ft)(sec) 900ft ρ == d dt 53 0.000556 1.7310slug/(ft)(sec) 32.2 ρ ==× d dt
5 2 (1716)(510)(1.7310)(0.0345)(1716)(0.0167) 16.1 15.10.9916.1lb/(ft)(sec) 2116 0.0076atm/sec ρ =×+ =+== = d dt 2.7 In consistent units, 10273263K=−+= T Thus, 4 3 /(1.710)/(287)(263) 0.225kg/m ρ ρ ==× = pRT 2.8 53 3 /0.510/(287)(240)0.726kg/m 1/1/0.7261.38m/kg ρ ρ ==×= === pRT v

Magnitude of the resultant aerodynamic force = 22 (6303)(835)6303.6lb

Minimum velocity occurs when sin θ = 0, i.e., when θ = 0° and 180°.

V

= 0 at θ = 0° and 180°, i.e., at its most forward and rearward points.

Maximum velocity occurs when sin θ = 1, i.e., when θ = 90°. Hence,

3 (85)(1)127.5mphat90, 2 θ ° V= ==

i.e., the entire rim of the sphere in a plane perpendicular to the freestream direction.

No
be
reproduced, or distributed in any form or by
means, without the prior written permission of the publisher, or used
the limited distribution to teachers and educators
by McGraw-Hill for their individual course preparation. A student using this manual
using it without permission. 4 2.9 33 00 23 0 Forceduetopressure (211610) [21165]6303lb perpendicular to wall. p F pdx xdx xx ====-= òò 33 τ 1 00 2 1 3 2 0 90 Force due to shear stress= τ (9) [180(9)]623.554083.5lbtangentialtowall. Fdxdx x x == + =+=-= òò
PROPRIETARY MATERIAL. © 2012 The McGraw-Hill Companies, Inc. All rights reserved.
part of this Manual may
displayed,
any
beyond
permitted
is
83.5 ArcTan0.76º 6303 θ R =+= æö ÷ ç == ÷ ç ÷ ÷ ç èø 2.10 3 sin 2 θ ∞VV =
min
max

2.11 The mass of air displaced is 3 (2.2)(0.002377)5.2310slug M

The weight of this air is 3 air (5.2310)(32.2)0.168lb W=´=

This is the lifting force on the balloon due to the outside air. However, the helium inside the balloon has weight, acting in the downward direction. The weight of the helium is less than that of air by the ratio of the molecular weights

4 (0.168)0.0233lb. 28.8 c WH ==

Hence, the maximum weight that can be lifted by the balloon is 0.168 0.0233 = 0.145 lb.

2.12 Let p3, ρ3, and T3 denote the conditions at the beginning of combustion, and p4, ρ4, and T4 denote conditions at the end of combustion. Since the volume is constant, and the mass of the gas is constant, then p4 = ρ3 = 11.3 kg/m3. Thus, from the equation of state, 72

2.13 The area of the piston face, where the diameter is 9 cm = 0.09 m,

(a) The pressure of the gas mixture at the beginning of combustion is 62

PROPRIETARY MATERIAL. © 2012 The McGraw-Hill Companies, Inc. All rights reserved. No part of this Manual may be displayed, reproduced, or distributed in any form or by any means, without the prior written permission of the publisher, or used beyond the limited distribution to teachers and educators permitted by McGraw-Hill for their individual course preparation. A student using this manual is using it without permission.

5
==´
444
ρ pRT===´ or, 7 4 5 1.310 129atm 1.0110 p ´ == ´
2 32 (0.09) 6.3610m 4 π A==´
(11.3)(287)(4000)1.310N/m
is
ρ pRT===´ The
634 33
FpA==´´=´ Since 4.45 N = l lbf, 4 3 1.2810 2876lb 4.45 F ´ ==
ρ pRT
The
734 44
FpA=´´´ 4 4 8.2710 18,579lb 4.45 F ´ ==
333 11.3(287)(625)2.0210N/m
force on the piston is
(2.0210)(6.3610)1.2810N
(b) 72 444 (11.3)(287)(4000)1.310N/m
===´
force on the piston is
= (1/310)(6.3610) = 8.2710N

2.14 Let p3 and T3 denote conditions at the inlet to the combustor, and T4 denote the temperature at the exit. Note: 62 34 410N/m pp==´

(a) 6 3 3 3 3

410 =15.49kg/m (287)(900) ρ p RT ´ ==

410 =9.29kg/m (287)(1500) ρ p RT ´ ==

(b) 6 3 4 4 4

2.15 1 mile = 5280 ft, and 1 hour = 3600 sec.

So: miles5280ft1hour 6088 ft/sec. hourmile3600 sec

A very useful conversion to remember is that 60mph88ft/sec =

also, 1 ft = 0.3048 m

PROPRIETARY MATERIAL. © 2012 The McGraw-Hill Companies, Inc. All rights reserved. No part of this Manual may be displayed, reproduced, or distributed in any form or by any means, without the prior written permission of the publisher, or used beyond the limited distribution to teachers and educators permitted by McGraw-Hill for their individual course preparation. A student using this manual is using it without permission.

6
æöæöæö ççç÷÷÷ = ççç÷÷÷ ÷÷÷ ççç÷÷÷ èøèøèø
ft0.3048mm
sec1ftsec æöæö ÷ ÷ç ç ÷ = ÷ç ç ÷ ÷ç ÷ ç ÷ ÷ èøçèø Thus ftm 8826.82 secsec = 2.16 miles88 ft/sec 6921015 ft/sec hour60 mph  =   miles26.82 m/sec 692309.3 m/sec hour60 mph  =   2.17 On the front face 55 (1.071510)(2)2.14310 N ff FpA==×=× On the back face 55 (1.0110)(2)2.0210 N bb FpA==×=× The net force on the plate is 55 (2.1432.02)100.12310 N fb FFF=−=−×=× From Appendix C, 1 4.448 N. f lb = So, 0.123105 2765 lb 4.448 F × == This force acts in the same direction as the flow (i.e., it is aerodynamic drag.)
8826.82

Introduction to Flight 7th Edition Anderson Solutions Manual

PROPRIETARY MATERIAL. © 2012 The McGraw-Hill Companies, Inc. All rights reserved. No part of this Manual may be displayed, reproduced, or distributed in any form or by any means, without the prior written permission of the publisher, or used beyond the limited distribution to teachers and educators permitted by McGraw-Hill for their individual course preparation. A student using this manual is using it without permission.

7
2 10,100 Wing loading43.35 lb/ft 233 W s === In SI units: 2 2 2 lb4.448 N1 ft 43.35 1 lb0.3048 m ft N 2075.5 m W s W s   =     = In terms of kilogram force, 22 1 k kg N 2075.5 211.8 9.8 N mm ff W s   ==     2.19 5 miles5280 ft0.3048 m mkm 437 7.03310703.3 hrmile1 ft hrhr V  == × =   0.3048 m Altitude(25,000 ft)7620 m7.62 km 1 ft  == =   2.20 3 ft0.3048 m mkm 26,000 7.925107.925 sec1 ft secsec V  == × =   2.21 From Fig. 2.16, length of fuselage = 33 ft, 4.125 inches = 33.34 ft 0.3048 m 33.34 ft10.16 m ft  ==   wing span = 40 ft, 11.726 inches = 40.98 ft 0.3048 m 40.98 ft12.49 m ft  ==  
2.18
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