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Program LRCDM2 : Improved aerodynamic prediction program for supersonic canard-tail missiles with axisymmetric bodies

Author:
Dillenius, Marnix F. E.
Published:
Apr 1, 1985.
Physical Description:
1 electronic document
Online Version

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Unclassified, Unlimited, Publicly available.
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Summary:
Program LRCDM2 was developed for supersonic missiles with axisymmetric bodies and up to two finned sections. Predicted are pressure distributions and loads acting on a complete configuration including effects of body separated flow vorticity and fin-edge vortices. The computer program is based on supersonic panelling and line singularity methods coupled with vortex tracking theory. Effects of afterbody shed vorticity on the afterbody and tail-fin pressure distributions can be optionally treated by companion program BDYSHD. Preliminary versions of combined shock expansion/linear theory and Newtonian/linear theory have been implemented as optional pressure calculation methods to extend the Mach number and angle-of-attack ranges of applicability into the nonlinear supersonic flow regime. Comparisons between program results and experimental data are given for a triform tail-finned configuration and for a canard controlled configuration with a long afterbody for Mach numbers up to 2.5. Initial tests of the nonlinear/linear theory approaches show good agreement for pressures acting on a rectangular wing and a delta wing with attached shocks for Mach numbers up to 4.6 and angles of attack up to 20 degrees.
Other Subject(s):
Collection:
NASA Technical Reports Server (NTRS) Collection.
Note:
Document ID: 19870019092.
Accession ID: 87N28525.
NAS 1.26:3883.
NASA-CR-3883.
NEAR-TR-287.
Terms of Use and Reproduction:
No Copyright.
View MARC record | catkey: 15697520