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本书为钱学森1947—1949年在麻省理工学院航空系教授可压缩流体气动力学课程的讲义，体现了当时前沿的空气动力学水平。全书共分19章。第1～4章为基本原理，给出可压缩流描述的基本参数和基本原则。第5～11章讨论相对简单的各种类型二维流动，从不可压无旋流动开始，到亚、跨、超、高超声速的各种处理方法，包括速度图法、相似律、线性化理论等。第12～16章针对不同翼型不同流速进行三维分析。第17～19章集中于黏性效应，涉及流体的黏性，速度与温度边界层、边界层与激波相互作用等。本书数学推导精致、内容翔实、物理概念明晰，在讲解理论知识的同时还传授了如何把握物理本质、建立数学模型的理念和方法。这对于当今工程或技术科学的学者仍具有现实意义。
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| 目錄：
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DIVISION ONEFUNDAMENTAL PRINCIPLES
Chapter 1Parameters in Compressible Flow００3
1.1Velocity of Sound and Mach Number００3
1.2Viscosity， Reynolds Number００4
1.3Heat Conduction， Prandtl Number００5
1.4Property of Gas， Ratio of Specific Heat００6
1.5Similarity of Flows００6
Chapter 2Steady OneDimensional Motion of a Perfect Compressible Fluid００8
2.1Thermodynamic Relations， and Energy Equation００8
2.2Perfect Gas Relations０10
2.3Flow Area， Conditions at the Throat０13
2.4Flow Through a De Laval Nozzle０15
2.5Pressure and Velocity Relations in Isentropic Flow０15
Chapter 3Shock Wave０19
3.1Relation of Quantities in front and behind the Shock０19
3.2Thickness of Shock０23
3.3Creation of Shock from Finite Compression Disturbances０25
3.4Oblique Shock０29
3.5Flow over a Wedge０33
3.6Pitot Tube０34
AppendixThe Concept of Entropy and the Second Law of Thermodynamics０36
Chapter 4Basic Equations of Motion of a Compressible， Inviscid and
NonHeat Conducting Fluid０38
4.1General Equations０38
4.2Kelvin Theorem０42
4.3Helmholtz Theorem０44
4.4Steady TwoDimensional Rotational Flow — Detached Shock０46
4.5Nonsteady Irrotational Flow０50
4.6Method of Approximate Solution of Irrotational Subsonic Isentropic Flow０51
AppendixVector Differentiation０53
DIVISION TWOTWODIMENSIONAL FLOWS
Chapter 5RayleighJanzen Method０59
5.1General Equations０59
5.2Solution by means of Complex Variables０61
5.3Flow around a Circular Cylinder０64
5.4Pressure Coefficient as a Series of Ma02０68
5.5Higher Order of Approximation for the Circular Cylinder０69
Bibliography０70
Chapter 6PrandtlGlauert Method０72
6.1Basic Equations for Iteration０72
6.2First Approximation — PrandtlGlauert Rule０76
6.3First Approximation， Using Velocity Potential０78
6.4Higher Approximations０80
Bibliography０81
Chapter 7Hodograph Method and KrmnTsien Approximation０83
7.1Basic Equations in Hodograph Variables０84
7.2Formulation of Problem in Hodograph Plane０89
7.3KrmnTsien Approximation０90
7.4Velocity and Pressure Correction Formulae０93
7.5Coordinate Correction０96
7.6Application to the Flow around an Elliptic Cylinder０98
7.7Further Development of KrmnTsien Approximation102
Bibliography102
Chapter 8
Velocity and Pressure Correction Formulae104
8.1Correction for Boundary Effects in Subsonic Flow104
8.2Limitations of the Correction Formulae107
8.3The Recommended Correction Formulae110
Bibliography113
Chapter 9Exact Solution of Isentropic Irrotational Flow114
9.1Flow with 180° Turn114
9.2Limiting Line119
9.3Breakdown of Potential Flow121
9.4General Exact Solutions123
Bibliography125
Chapter 10
TwoDimensional Supersonic Flows127
10.1The Lost Solution127
10.2PrandtlMeyer Flow130
10.3Flow over an Airfoil131
10.4Ackerets Formulae134
10.5Further Remarks136
Bibliography136
Chapter 11
Transonic and Hypersonic Similarity Laws138
11.1Transonic Flow Equation138
11.2Transonic Similarity Law142
11.3Slightly Supersonic Flow143
11.4Hypersonic Flows and Similarity Laws148
Bibliography152
Chapter 12Linearized Theory of Flow over a Slender Body of Revolution153
12.1Subsonic Flows with Axial Symmetry153
12.2Linearized Subsonic Flow154
12.3Subsonic Flow over a Slender Ellipsoid of Revolution157
12.4Supersonic Flow over a Slender Body of Revolution159
12.5Pressure Distribution163
12.6Wave Drag165
12.7Origin of Wave Drag — Transfer of Momentum167
12.8Body of Minimum Wave Drag168
12.9Lift of a Body of Revolution171
Bibliography174
Appendix175
CHAPTER 13
NonLinear Theory of Axially Symmetric Flows176
13.1Transonic Similarity Law176
13.2Hypersonic Similarity Law179
13.3“Lost Solution” of the Exact Equation181
13.4Exact Solution for Flow over a Cone182
Bibliography184
Chapter 14
Similarity Laws for
Wings of Finite Span186
14.1Similarity Law in Subsonic Flow186
14.2Similarity Law in Transonic Flow190
14.3Similarity Laws in Supersonic Flow193
14.4Similarity Laws in Hypersonic Flow194
Chapter 15
Rectangular Wing in Supersonic Flow197
15.1Source and Doublet Distribution197
15.2General Relation Between Source Distribution and Thickness Distribution of the
Wing201
15.3Rectangular Wing at Zero Angle of Attack — Drag Problem203
15.4Drag of Rectangular Wing at Very Small Aspect Ratio 207
15.5Lift Problem of a Rectangular Flat Plate208
15.6General Relation Between the Doublet Distribution and the Lift
Distribution214
15.7Aerodynamic Characteristics of a Rectangular Wing215
Appendix218
Chapter 16
Linearized Supersonic Wing Theory219
16.1Swept Wings of Infinite Span219
16.2Triangular Source Distribution221
16.3Arrowhead Wings224
16.4Reverse Flow Theorems228
16.5Conditions of the Edges of a Wing230
16.6Flow behind the Wing232
Bibliography233
Chapter 17Flow of a Viscous Compressible Fluid237
17.1Stresses and their Equations of Transformation237
17.2Rates of Strain and their Equations of Transformation239
17.3Relation between Stress and Rate of Strain241
17.4Justification of the StressStrain Relation244
17.5NavierStokes Equations246
17.6Energy Equation248
Chapter 18Boundary Layer251
18.1Boundary Layer Equations251
18.2Steady Flow in Boundary Layer and TemperatureVelocity Relation254
18.3Boundary Layer without Pressure Gradient257
18.4Approximate Solution of Boundary Layer over a Flat Plate259
18.5Cooling by Radiation262
18.6Steady Boundary Layer over a Body of Revolution263
18.7Integral Theorems267
18.8Stability of Laminar Boundary Layer and Turbulent Boundary Layer 270
Bibliography271
Chapter 19
Interaction of Boundary Layer and Shock273
19.1The λShock and the Simple Shock273
19.2Applications of the Concept of Softening of Shock275
Bibliography276
Appendix AProblems277
Appendix BExam283
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我老师钱学森博士毕业后先是留在加州理工学院工作，后由其导师冯·卡门推荐任教于麻省理工学院，而师弟兼挚友郭永怀则应邀去康奈尔大学任教。于是钱学森驱车从加利福尼亚州的帕萨迪纳出发，先是送郭永怀到纽约州的伊萨卡，然后自己再开车到位于波士顿的麻省理工学院。
我赴美留学之际，美国组装的V2火箭发射成功，自制的探空火箭“女兵下士”上天。波音公司造出了跨声速的后掠翼B47轰炸机，美国空军也突破音障，造出了X1、X2超声速战机。于是高速空气动力学成为的热门，这本书就是钱先生在麻省理工学院讲授可压缩流体气动力学的讲义。
此前钱学森应冯·卡门之邀，参加了美国军方[陆军航空兵（AAF），后于1947年9月18日独立成为美国空军（USAF）]科学咨询团，并赴德国进行了考察，掌握了大量资料，所以在讲义编写中他能居高临下、精挑细选，兼顾理论与实际应用。本书以阐述基本原理为主，数学推导极其精致，由浅入深，内容翔实，非现今教科书可比，而且包括了诸如有限翼展、三角翼、“卡门钱近似”公式细节等众多一般书籍不会涉及的内容，故虽完成于七十余年前，然其内容至今仍未过时。行文至此不由想起自己当年在加州理工学院接受钱老的耳提面命、日夜苦读的情景，今年是钱老110周年诞辰，我们翻译出版这本讲义以资纪念，前日又闻中国卫星完成月球背面之旅，希望我辈的成绩能告慰钱老的在天之灵。
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