Separated Flow Over Bodies of Revolution Using an Unsteady Discrete-vorticity Cross Wake: Computer program description, Part 2A method is developed to determine the flow field of a body of revolution in separated flow. The computer was used to integrate various solutions and solution properties of the sub-flow fields which made up the entire flow field without resorting to a finite difference solution to the complete Navier-Stokes equations. The technique entails the use of the unsteady cross flow analogy and a new solution to the two-dimensional unsteady separated flow problem based upon an unsteady, discrete-vorticity wake. Data for the forces and moments on aerodynamic bodies at low speeds and high angle of attack (outside the range of linear inviscid theories) such that the flow is substantially separated are produced which compare well with experimental data. In addition, three dimensional steady separated regions and wake vortex patterns are determined. The computer program developed to perform the numerical calculations is described. |
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AATACK ADDXI ADYNF AKDOT AKHALF ALPHA angle of attack APPENDIX approximation ARIGHT ARITH BLBO BLBOX body geometry body length boundary layer CADRE calculate CARD coefficient COEFL Columns Variable Value COMPUTE CONTINUE VCF8 cylinder DEBUGGING AND TESTING DELT DIMENSION Dimensional body ERRER ERROR FEXTRP finite difference FORMAT FREEV FREEVTX FXDKNT GAMMA GO TO 20 grid IDIM IFLAG Input array INTEGRAL INTEGRAND INTERV ISTAGE JADD JDIM KFINAL KNOT KPUN MODE NDIM NOKNOT NONDI nondimensional normal force parameters PDRAG point vortex POTFL printed output PROGRAM VCF punched RETURN END RITE RSEP RVTX RZERO RZRO SECON separation angle SPLIN SQRTPI SUBINTERVAL subprograms SUBPROGRAMS CALLED SUBROUTINE TAPE TEMPORARY DEBUGGING TESTING OUTPUT THETA THTA TRAPEZOID SUMS TRID UAPRX1 VCF8 VINT VMFIX VORDL vortex locations vortices WRIT WRITE WRTO XDOT XDOTB XKNOT XRDOT YDOT YDOTB ZSTAR