1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
61
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
83
84
85
86
87
88
89
|
{
"metadata": {
"name": "",
"signature": "sha256:803218956e8d07c2bbc2005621cfab4517eff6a55bb3c468628e715c71e6bf8d"
},
"nbformat": 3,
"nbformat_minor": 0,
"worksheets": [
{
"cells": [
{
"cell_type": "heading",
"level": 1,
"metadata": {},
"source": [
"CHAPTER11:SUBSONIC COMPRESSIBLE FLOW OVER AIRFOILS LINEAR THEOREY"
]
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Example E01 : Pg 382"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"# All the quantities are expressed in SI units\n",
"import math \n",
"Cp_incompressible = -0.3; # Cp for incompressible flow\n",
"M = 0.6; # Mach number\n",
"# Thus from eq.(11.52)\n",
"Cp_compressible = Cp_incompressible/math.sqrt(1-M**2);\n",
"print\"(a)The Cp after compressibility corrections is:\",Cp_compressible,\"Cp\""
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"(a)The Cp after compressibility corrections is: -0.375 Cp\n"
]
}
],
"prompt_number": 1
},
{
"cell_type": "heading",
"level": 2,
"metadata": {},
"source": [
"Example E02 : Pg 383"
]
},
{
"cell_type": "code",
"collapsed": false,
"input": [
"# All the quantities are expressed in SI units\n",
"import math \n",
"cl_incompressible = 2*math.pi; # lift curve slope\n",
"M_inf = 0.7; # Mach number\n",
"# from eq.(11.52)\n",
"cl_compressible = cl_incompressible/math.sqrt(1-M_inf**2); # compressible lift curve slope\n",
"print\"(a)The cl after compressibility corrections is: cl =\",cl_compressible,\"alpha\""
],
"language": "python",
"metadata": {},
"outputs": [
{
"output_type": "stream",
"stream": "stdout",
"text": [
"(a)The cl after compressibility corrections is: cl = 8.7982192499 alpha\n"
]
}
],
"prompt_number": 2
}
],
"metadata": {}
}
]
}
|
