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Create first geometry file „01.dat” . File will contain symmetrical fuselage with wing part and complete tail unit. The „01.dat” file must have vortex wake generated. Step 2 Important note: The wing part cannot be closed with rib because the next grid part will be connected to it. In aircraft *.ms2 definition file choose: 0 – don’t close wing with rib Fig. 62. Fig. 62 – *.dat file – next part of the complicated grid file (wing & nacelle part – left side) Next geometry „02_L.dat” file contains right nacelle part, part of wing (not closed with rib) and generated wake. Not symmetrical grids can be made by changing the proper flag in *.ms2 file section. Nacelle is made similarly like fuselage. Important note: Changing the proper flag in MAIN FILE SCTION in *.ms2 file [1.3.1], we can easily create (not symmetrical) left or right side of model/ body. Step 3 Fig. 63 – *.dat file – next part of the complicated grid file (wing end & nacelle part – right side) Next geometry „03_L.dat” file contains left nacelle part and right wing ending. The „03.dat” file must have vortex wake generated. 58
Step 4 Right side of the object is made similarly! Fig. 64 – Complicated grid elements (right side) When we have all grid elements, we are ready to connect them into one complicated grid file. We will use CONNECT TWO GRIDS [4.1] function. To connect grids properly we need to know their exact position in global coordinate system. This is an example grid connection procedure: Fig. 65 – Connect operations number 1 Fig. 66 – Connect operations number 2 59
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Version ENGV1 Warsaw, 01-04-2010 1
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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 and 10: - lift force - drag force The aerod
Page 11 and 12: 1.2.3. Main computational subprogra
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: 4.2. Creation of complex computatio
Page 61 and 62: Important notes: What we should kno
Page 63 and 64: Main program options: Folder path f
Page 65 and 66: 4.4. How to export geometry from UG
Page 67 and 68: Remember: don’t insert DATUM PLAN
Page 69 and 70: In some fuselage areas you will hav
Page 71 and 72: Fig. 86 - Models prepared with the
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