PANUKL Help - ITLiMS

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1.2. Brief PANUKL software description – main subprograms and their functionalities PANUKL 2002 application is composed of three main subprogram groups. In first group we can find data preparation programs. In second group we can find programs to process and compute data. The last group is the managing program where we can watch obtained results and make appropriate changes and modifications. PANUKL works in Windows and Linux: o MS Windows (2000/XP/Vista), o Linux (extra information can be found in installation package). Both program versions need OpenGL libraries. 1.2.1. Managing subprogram – GRIDVIEW GRIDVIEW All of PANUKL 2002 subprograms can be executed from GRIDVIEW – PANUKL’s managing application (for detailed description go to chapter 3). From CREATE menu (one of the managing application menus) we can access to subprograms. We can also run subprograms from command line. Each subprogram needs a configuration file (see below). The correct order is necessary during computation process. 1. MESH – grid generator (run: Mesh.exe name.ms2), 2. NEIGH – vortex wake and neighbor generator (Neigh.exe name.ngh), 3. PANUKL – velocity potential distribution solver (Panukl.exe name.par), 4. PRESS – pressure distribution and global aerodynamic results solver (Press.exe name.prs). 1.2.2. Data preparation subprogram – MESH MESH MESH subprogram is being used to create grid (made from quadrangle panels) describing aircraft body. To create grid file [name.INP] user must prepare correct input files: main aircraft geometry description file [name.MS2] (contains aircraft reference data, information about wing, tail , fuselage overall geometry), wing airfoil geometry file [name.PRF], fuselage geometry file [name.F]. For more information go to chapter 1.3.1. 10
1.2.3. Main computational subprograms – NEIGH, PANUKL and PRESS NEIGH NEIGH subprogram is being used to calculate neighboring panel numbers. Additionally it extends grid with wake grid panels. The input file for NEIGH is [name.INP] - grid geometry file. Configuration file is [name.NGH]. The output file with grid and wake panels is [name.DAT]. PANUKL PANUKL subprogram computes influence factors, missing geometrical data and solves system of equations. As a result we get velocity potential distribution. PANUKL subprogram input parameters like angle of attack or angular velocities are read from [name.PAR] configuration file. The results are saved to [name.PAN] output file which is an input for PRESS subprogram. Creating [name.PAN] output file can last long and it is the most CPU consuming process. PRESS PRESS subprogram computes pressure distribution over the aircraft body by differentiating the velocity potential distribution. Additionally we can obtain global aerodynamic coefficient values, downwash distribution and inducted drag in Trefz plane. PRESS subprogram input parameters are read from [name.PRS] configuration file. The results are saved to three output files (for more information go to chapter 1.3.2). [name.OUT] - global aerodynamic results, [name.CZY] - aerodynamic coefficient distribution over the wing, [name.TXT] - the results for pressure coefficient, velocity, source or doublet distribution etc. (for each panel of aircraft body), [name.EPS] - downwash results (created as an option), [name.BLN] - object geometry outline for current downwash computational plane (created as an option). 11
Page 1 and 2: Version ENGV1 Warsaw, 01-04-2010 1
Page 3 and 4: 3.3. Data flow In PANUKL during the
Page 5 and 6: 1.1.2. Introduction The develop of
Page 7 and 8: Fig. 1 - Approximation of the body
Page 9: - lift force - drag force The aerod
Page 13 and 14: File [name.f] - fuselage geometry -
Page 15 and 16: File [name.ms2] - complete aircraft
Page 17 and 18: ottom # key word „bottom” or
Page 19 and 20: Fig. 6 - The example of „independ
Page 21 and 22: File [name.TXT] The results for pre
Page 23 and 24: File [name.CZY] Aerodynamic coeffic
Page 25 and 26: Fig. 13 - Destination Folder select
Page 27 and 28: 2.2. PANUKL installation guide in L
Page 29 and 30: Available options in FILE menu) Fun
Page 31 and 32: 3.1.2. DRAW menu description Availa
Page 33 and 34: Fig. 28 - Creating grid file for cu
Page 35 and 36: Trailing edge angle [deg] Neighbour
Page 37 and 38: Fig. 32 - Creating *.pan file Fig.
Page 39 and 40: Fig. 34 - Creating output result fi
Page 41 and 42: Downwash calculation: Number of mes
Page 43 and 44: Fig. 38 - External XFOIL program wi
Page 45 and 46: Fig. 41 - Selecting result file wit
Page 47 and 48: 3.1.6. TOOLS menu description Avail
Page 49 and 50: Fig. 48 - Graphic representation of
Page 51 and 52: 3.2. Computational procedure - diag
Page 53 and 54: 3.3. Data flow In PANUKL during the
Page 55 and 56: How it Works ? Option 1 - we do hav
Page 57 and 58: 4.2. Creation of complex computatio
Page 59 and 60: Step 4 Right side of the object is
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Important notes: What we should kno
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Main program options: Folder path f
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4.4. How to export geometry from UG
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Remember: don’t insert DATUM PLAN
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In some fuselage areas you will hav
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Fig. 86 - Models prepared with the
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