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  For a two-dimensional rectangular wing having a NACA 23012 airfoil, the
critical Mach number is 0.672 and the lift-curve slope is 0.104/deg. What should
be the leading-edge sweep angle to have a critical Mach number of 1.5? What is
the lift-curve slope of this swept wing?
So/ution. Wehave
M,r,s =  M A
cosA -- _Mcr
  =M
 0.672
      = ~5
        - 0.448
A - 63.3845 deg
The lift-curve slope is. given by
                                                    aos - a cos A
                                                                              - 0.104 * 0.448
                                       - 0.0466/deg
1:13 Summarlv
      In ttus chapter, we reviewed the basic principles of aerodynamics applicable to
aircraft. We studied elements of the fiuid flow over wings and bodies at subsonic,
REVIEW OF BASIC AERODYNAMIC PRINCIPLES                65
transonic, and supersonic speeds and understood how lift, drag, and pitching mo-
ments vary with angle of attack and Mach number. This aerodynamic background
slriould be useful in the study of performance, stability, and control of the aircraft,
which will be discussed in the next chapters of this text
References
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  2Abbott, I. H., and Von Doenhoff, A. E., Theory of Wing Sections, Dover, New York,
1959.
  .3Perkins, C; D., and Hage, R. E*,Airpkme Perj'ormance, Stability cmd Control, 10th ed.,
Wiley, New York, 1965.
     4Jacobs,E. W., and Sherman, A.,l*Airfoil Section Characteristics as Affected by Variations
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Geometric Design in a Wholly Subsonic Flow:'Boundary Layer and Flow Control, Vol. l,
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   7Kucthc, A. M., and Schetzelr, J. D., Foundations of Aerodynamics, 2nd ed., Wiley, New
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    8Multhopp, H.,IIMethods for Calculating the Lift Distribution ofWings (Subsonic Lifting
Surface Theory):' ARC R and M 2884, 1950(U).
      9Fallmer, V. M., "The Calculation ofthe Acrodynamic Loading on Surface of Any Shape:'
ARC R and M 1910, 1943GD.
   loDe Young, J., and Harper, C. W., "Theoretical Symmetric Spanwise Loading at Subsoruc
Speeds for Wrngs Having Arbitrary Planform:' NACA TR 921, 1948(U).
 iiNeumark, S.,"'Critical Mach Numbers for Thin Untapered' Swept Wings at Zero
Incidence:' ARC R and M 2821,  1954(U).
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sonic Speed for Wing jfip Mounted Winglets," NASA TND-8260, 1976.
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ICAS, Haifa, Israel, 1974.
 14Rao, D. 1VL, and Kariya, T. T., "Boundary-Layer Submerged Vortex Generators for
Separation Control-An Exploratory Study:' Proceedings of lst National Flui'd Dynamic
Conference, Cincinnatti, OH, 1988, pp. 839-846.
  tsMaltby, R. L., "The Development of the Slender Delta Concept," Aircralt Engineer:ing,
March 1968, pp. 12-17.
16Polhamus, E. C., "Vortex Lift Research, Early Contributions and Some Current
Challenges:' NASA CP-2416, Vol. 1, 1992.
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Paper 83-1834, 1983.
    18Murri, D. G., Nguyen, L. T., and Grafton, S. B., "Wind Tunnel Free-Flight Investigations
　
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