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CHAPTER 1
1.1
(a)
4
p 1.9 10 3
0.326 kg/m
RT (287)(203)
ï‚´
ï²   
(b)
 
3
p 1058 T 501 R
ï²R 1.23 10 (1716) ï€Â
   
ï‚´
1.2
 
TE
u u u LE
N p cos sin ds ï‚¢  ï±  ï´ ï± 
 
TE
LE
 p cos sin ds ï± ï´ ï± 
(1.7)
ds cos dx ï±  ds cos dy ï±  ï€Â
Hence,
   
TE TE
u u LE LE
N p p dx dy ï‚¢   ï´  ï´        
TE TE
u u LE LE
N p p p p dx dy ï‚¥ ï‚¥   ï´  ï´   
ï‚¢
  
Divide by q S q c(1) ï‚¥

ï‚¥
TE TE
u u
LE LE
N 1 1 p p p p dx dy
q c c q q c q q
ï´ ï´ ï‚¥ ï‚¥
ï‚¥ ï‚¥ ï‚¥ ï‚¥ ï‚¥
        ï€Â
       
ï‚¢
                 u n e
c TE
n p p f f 0 LE
1 1 c c c dx c c dy
c c e
    
This is Eq. (1.15).
For Fundamentals of Aerodynamics, 7th Edition John Anderson Chapter 1-19 Complete And Study material 269pages LEARNEXAMS
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