82 



HYDRODYNAMICS 1\ Mill' 1)1 SKiX 



Src. -14.9 



l>nck of the ncvenil nootions shows wide vtiri:iti<iii!< 

 for tho oxtn-mc vmIuci of real-slip nitio roprescnte*! 

 in the ti-st. 



(2) Jones, B. M., nml Piitenion, C. J., "InvostiRation of 



the Diiitribution of Pressure over the Entire Surface 

 of an Aerofoil," Teeh. Rep. Adv. Comm. for Aero 

 for 1912-1913 (Kngland), R and M 73, Mar 1913, 

 pp. 97-lO.S 



(3) Norton, F. H., and Bacon, D. L., "Pressure Distri- 



bution over Thick Airfoils— Model Tests," NACA 

 Rep. 150, 1922, pp. -I.'il-ITI. On pp. 451-J52 there 

 is a list of a numlicr of prior references on pressure 

 distribution over airfoils. 



(4) Fage, .\., and Howard, R. G., "A Consideration of 



.Virscrcw Theory in the Lisht of Data Derived 

 from an Experimental Investigation of the Distri- 

 bution of Pressure over the Entire Surface of an 

 Airscrew Blade, and also Over .Verofoils of Appro- 

 priate Shapes," .\RC, R and M 6S1, Mar 1921, pp. 

 264-357. Pres-sure measurements were taken on a 

 full-size airscrew, one point at a time. 



(5) Briggs, L. J., and Dryden, H. L., "Pressure Distribu- 



tion Over Airfoils at High Speeds," NACA Rep. 

 255, 1926 



(6) Fage, A., "The Flow of Air and of an Inviscid Fluid 



.\round an EUiptic Cylinder and an Aerofoil of 

 Infinite Span, Especially in the Region of the 

 Forward Stagnation Point," Tech. Rep. Aero. 

 Res. Comm. (England), 1927-1928, Vol. I, R and 

 M 1097, Jul 1926, pp. 61-80 



(7) Perring, W. G. A., "The Theoretical Pressure Distri- 



bution Around Joukowski Aerofoils," Tech. Rep. 

 Aero. Res. Comm. (England), 1927-1928, Vol. I, 

 R and M 1 106, May 1927, pp. 209-221 



(S) Perring, W. G. A., Discussion, INA, 1928, Fig. B on 

 p. 253 



(9) Knight, M., and Loc.ser, O., Jr., "Pressure Distribu- 

 tion over a Rectangular Monoplane Wing Model 

 Up to 90 Degrees Angle of Attack," N.\CA Rep. 

 288, 1928 



(10) Gutsche, F., "Versuchc an Propellerblattschnittcn 



(Tests on Propeller Blade Sections)," Schiffbau, 

 1 Aug 1933, pp. 267-270; 15 Aug 1933, pp. 286-289. 

 The latter group of pages contains many graphs of 

 pres-sure distribution on airfoil section.^. 



(11) Schoenhcrr, K. E., SXAMi;, 1934, p. 90. Contours 



for pressure minima in terms of (1) Ap/g, (2) 

 thickness ratio, and (3) lift coefficient, for ogival 

 and airfoil sections, respectively, arc given in 

 Figs. 19 and 20, pp. 109-112. 



(12) Winter, H., "Flow Phenomena on Plates and .\irfoils 



of Short Span," NACA Tech. Memo 798, Jul 1930, 

 pp. 7-9 and Figs. 21-24 



(13) Shannon, J. F., and Arnold, R. N., "Statistical and 



Experimental Invostigalions on tho Singing 

 Propeller Problem," lESS, 193H-1939, Vol. 82, 

 pp. 255-374, esp. pp. 270-285, 326 



(14) Schoenhcrr, K. E., PNA, 19.39, Vol. 11, Fig. 29, 



p. 176. Thiti diagram give.n the pre.Hsure distribuliun 

 along the chord of a hydrofoil (or airfoil) wrction 

 at nn K.6Hlegre<.- angle of attack. 



(15) Goodttll, Sir Sliinli-y V., "Sir Charles Parsons and 



the Royal Navy," INA, Apr 1942, pp. 1-10, esp. 

 Fig. 6, p.|3; SCO also HBHR, 23 Apr 1942, p. 451 



.11.. Villi Liiinimrrii, \V. P. A., lU'SS, 1948, Fig. 104, 

 p. 101 



(17) Hill, J. G., "Tho Design of Propcllors," SNAME, 



1949, Fig. 11, p. 151. This diagram shows the 

 graphs of pressure coclTicient Ap/7, on a base of 

 per cent of chord from the leading edge, for tho 

 backs of two N.\C.\ sections with two difTereot 

 camber ratios and two angles of attack. 



(18) Reed, T. G., and Ormsby, R. B., Jr., "The AVA 



Method of Calculating Pressure Distributions Over 

 Profiles of Arbitrary Shape (Including a Transla- 

 tion of 'l;ber die Berechnung der Druckvertcilung 

 von Profilen,' by F. Riegels, Technische Berichtc, 

 1943, Vol. 10)," TMB Aero. Memo 28, Mar 1955. 



44.9 Velocity and Pressure Fields Around a 

 Hydrofoil. In Fig. 44. E of Sec. 44. G there are 

 ])ii'Uirp(i two flow pattern.s around a tj'pical sym- 

 iiiotric airfoil or hydrofoil, one corresponding to 

 the flow of an ideal lifiuid and one of a real liquid. 

 Tables 44. b and 44. c of that section list references 

 to diagrams and flow patterns around other 

 airfoils and hydrofoils, made up generally of 

 streamlines. However, the designer can often use 

 to advantage a chart or plot embodying isobars 

 and isotachj'ls, to show the essential characteristics 

 of the pressure and velocity fields around the foil. 



Unfortunately, the published data on this 

 particular item are very meager and there appear 

 to be no distribution plots that can be taken as 

 typical. Most of the data apply to airfoils, of the 

 customary asymmetric .sections used for airplane 

 wings. Thej' were taken usually to indicate 

 acceptable positions for the pitot tubes of air- 

 speed meters, and so do not cover the fields sur- 

 rountiing the airfoil as a whole. 



A few references indicate sources of some of the 

 published results for projects of this kind: 



(1) Piercy, N. A. V., and Richardson, E. G., "On the 



Flow of Air Adjacent to the Surface of an .\ero- 

 foil," ARC, R and M 1224, Dec 1928, pp. 32f.-34S 



(2) Tanner, T., "The Two-Dimcnsional Flow of Air 



Around an .\crofoil of Symmetrical Section," ARC, 

 R and M l.!.">3, Jul 1930, pp. 100-116 



(3) Parsons, J. F., "Full-Scale Wind-Tunnel Tests to 



Determine a Satisfactory Location for a Service 

 Pitol-Stalic Tube on a Low-Wing Monoplane," 

 NACA Tech. Note 501, Mar 1936 



(4) Gates, S. B., and Cohen, J., "Note on the Standardisa- 



tion of Pilot-Static Head Position on Monoplanes," 

 ARC, R and M 177S, Jan 1937, pp. 1238-1251 



(5) Crablw, E. R., and Diproso, K. V., "Calculated 



Pri'».sures /Vhcad of Struts and Wings," R..\.E., 

 Farnborough (Engliiiun, Ti'chiii.-al Note .Xero 1510, 

 Oct 1944 



(6) Kuethr, A. .M., M.K.-.-, P. U., .•m.l Curry, U . II., 



"Measurements in the Boundary Ijiycr of a Vawcil 

 Wing," NACA Tech. Note 1946, Sep 1949. 



