Y/The NSWC Aeroprediction Code has been extensively ipplied to the prediction of static and dynamic aerodynamics '0/ mTisSit configurations.Major extensions have recently been nfiade to the code to extend its capability to 0/,/' M , < 8 and 0P 1 8 0 d and also to improve the tranaonic inviscid ýo'ay alon static aerodynamic predictions and the dynamic derivative predictions for all Mach numbers.The theoretical basis for the code extensions are outlined and previous methods are briefly reviewed.The code is evaluated through comparisons of computational examples with experiment for body alone, body-tail and body-tail-canard configurations.The speed and accuracy of the code are ideal for use in preliminary design.Examples of design applications to specific tactical weapon configurations are presented.-.
('"" INTRODUCTIONA continuous need exists for estimating the aerodynamic characteristics of a wide variety of tactical missile and projectile configurations, especially in the preliminary or conceptual design phase.To meet this need, the Navy (in cooperation with the Army) undertook the development of a rapid, inexpensive, easy to use Aerodynamic Prediction Code in 1971.The code was developed so as to handle fairly general wing-body-tail configurations and hence have direct application to a high percentage of tactical weapon designs. Preliminary versions of the code were published in 1972, 1975, and 1977.The changing mission requirements for both current and future weapons has dictated, however, the need to revise and extend the capabilities of the 1977 version of the Aeroprediction Code, which was limited to M < 3.0 and small angles-of-attack (a < 150), to higher Mach numbers and anglesc-of-attack.The objective of the current effort, which is nearing completion, is to extend the 1977 version of the Aeroprediction Code to M = 8 and a -180@. L" In addition, modification of some of the existing methods due to advances in -J the state-of-the-art and computer program optimization is desirable.
0309 ()62T r-mt -i" bfn upproved 1-39The general approach of the code development has been to combine existing and newly developed computational methods into a single computer program. The basic method is that of component superposition where the body-alone, liftingsurface-alone and interference contributions are added to obtain total configuration aerodynamics.The code development has occurred in four increments. The first thrae of these increments were previously reported, and led to the development of a code capable of determining the aerodynamic coefficients for axisymmetric, non air-breathing configurations with up to two sets of lifting surfaces for low angles-of-attack and Mach numbers to 3.0.The results of the fourth increment, required to meet the stated objective, is the subject of this paper. Program plans for this effort and so e early results were presented at the l1th Naval Symposium on Ballistics. The theorigs used, outlined briefly here, are discussed in more detail elsewhere. ' The resulting code has compu...
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