Supercritical Wing Sections III by Frances Bauer

By Frances Bauer

The function of this e-book is to survey computational circulate learn at the layout and research of supercritical wing sections supported through the nationwide Aeronautics and area management on the power examine and improvement management arithmetic and Computing Laboratory of latest York college. The paintings used to be played below NASA offers NGR 33-016-167 and NGR 33-016-201 and ERDA agreement EY-76-C-02-3077. machine courses to be indexed and defined have purposes within the learn of flight of recent airplane at excessive sub­ sonic speeds. one of many codes generates cascades of shockless tran­ sonic airfoi~s which are anticipated to extend considerably the effici­ ency of compressors and generators. strong simulation of bodily saw flows has been completed. This paintings is a sequel to 2 prior books [1,2] released by means of Springer-Verlag less than comparable titles that we will consult with as Volumes I and II. long island November 1977 desk OF CONTENTS I. advent 1 1. Shockless Airfoils and Supercritical Wing Sections 1 2. Differential Equations of gasoline Dynamics 2 II. the tactic OF advanced features five 1. a brand new Boundary worth challenge five 2. Topology of the trails of Integration eight three. Iterative Scheme for the Map functionality nine III. TRANSONIC AIRFOIL layout CODE 10 1. remoted Airfoils 10 2. Compressor Cascades 12 three. Turbine Cascades thirteen four. comparability with test 14 IV. TWO-DU1ENSIONAL research CODE sixteen 1. Wave Drag sixteen 2. a quick Solver 19 three. comments approximately three-d movement 24 V. REFERENCES 26 VI.

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0 0 W W 0 LL Cl 0 ::E a:: 0 LL ell 0- ~ I- Q... Z ...... 0 -Cl LIJ a... ::J 0 3: (f) Ii) C\J I- :::t: ::::l 0.. z LIJ Ii) a:: 0 ::::l .... ) LL Ii) tO c:J 0 Ii) ...... 0 ...... Ii) 0 0 ..... J Ii) 0 ..... 479 FIGURE 2. 479 FIGURE 3. 189 FIGURE 4. 189 FIGURE 5. 831 FIGURE 6. 000 FIGURE 7. 110 PATHS OF INTEGRATION FOR SYMMETRIC AIRFOIL 54 B. Figures 8-13 The input speed distribution for the compressor cascade shown in Figures 8 and 9 was taken from an example prepared, using an earlier version of the design code [23], for Pratt and Whitney Aircraft and tested by the DFVLR in Germany (see also Figure 31).

32. , "Geometry of the complex characteristics in transonic flow," Comm. Pure Appl. , Vol. 21, 1968, pp. 175-185. 33. Whitcomb, R. , "Review of NASA supercritica1 airfoils," Ninth International Congress on Aeronautical Sciences, Haifa, 1974. VI. 1. USERS MANUAL FOR THE DESIGN CODE Introduction This chapter is intended for users of the new design program. is essentially independent of the material discussed earlier. It After studying it readers should be able to run the program effectively. The code, written in Fortran IV, has been run on the CDC 6600 at the Courant Institute to design isolated airfoils and compressor and turbine cascades.

VARIABLE NAMED WAS NOT FOUND 18. vlT DID NOT CONVERGE, HT = 19. NEWTON ITERATION FOR SONIC POINT DID NOT CONVERGE WELL 7. Glossary of TAPE7 Parameters All TAPE7 input parameters are listed below with the proper name, default value, definition, and usage. The order corresponds to the frequency of use in the examples we ran. written DEFAULT VALUE RECOMMENDED. In certain cases we have The user is strongly advised to use the default values for those parameters, especially if there is any difficulty.

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