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Step 5 Fig. 67 – Connect operations number 3 Fig. 68 – Connect operations number 4 After the last connect operation we must check the new grid with – CORRECT NEIGHBOURS [3.1.4] function to avoid grid errors. Fig. 69 – Generated complicated grid + example results The complicated grid is ready to proceed with farther analysis. 60
Important notes: What we should know before we will start to connect grids. Connected grid elements cannot be closed and must have the same division, e.g., two wing grid parts must have in connection area the same airfoil and its chord division and chord length. Connected grid elements must have one common plane. With this connection procedure we can create difficult grids that are not symmetrical. To make not symmetrical fuselage or nacelle we must remember to have the same number of sections/ frames for both sides. Section/ frame location must be also the same for both fuselage or nacelle parts. Fuselage or nacelle section/ frame number and location must be the same for left and right part. Sometimes we can simplify the geometry to connect two grids, e.g. wing body intersection area. Fig. 70 – Grid trick – easy to create wing body intersection area 61
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Version ENGV1 Warsaw, 01-04-2010 1
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3.3. Data flow In PANUKL during the
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1.1.2. Introduction The develop of
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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 and 58: 4.2. Creation of complex computatio
Page 59: Step 4 Right side of the object is
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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