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IMPORTANT NOTES: Fig. 5 – Fuselage geometry definition Fuselage geometry is described with fuselage frames/ sections. The stringer which intersects the first leading edge or wing/ horizontal tail point, separates into two extra stringers which pass round the wing. Those extra stringers are defined in fuselage geometry file and they are count to the max. stringer number for current fuselage. Point numbering order is not the same for frames and stringers, Fig. 5 First and last fuselage frame/ section reduce to a point. Y coordinate for points defining fuselage frames/ sections can’t be negative. Y coordinate for the first and last point on a single frame/ section must be the same. 14
File [name.ms2] – complete aircraft model – file description # - comment line (not necessary) # MAIN FILE SECTION begin # key word 26.6 # wing area (REAL) 1.91 # wing MAC (REAL) 8.56 # wing span (REAL) 6.43 # x coordinate for 0.25 MAC (REAL) 0.00 # z coordinate for 0.25 MAC (REAL) 1 # model scale factor (INTEGER) ***** # key separation signs test_01 # output file name „*.inp” AIRCRAFT GEOMETRY FILE EXAMPLE 2 # number of independent wings, this wing has got defined distribution along chord and it forces its distribution over the fuselage-wing penetrate area (e.g.: fuselage gets the section/ frame distribution from wing). 1 # number of dependent wings, this wing hasn’t got defined distribution along chord. It gets its distribution from the neighboring geometry (e.g.: wing gets the chord distribution from fuselage sections/ frames). 0 # object symmetry flag, „0” – object is symmetrical, „1” – only right half is taken into account, „-1” – only left half is taken into account during analysis. end # key word # WING SECTION – WING „0” begin_wing0 # wing No. „0” start section – main wing 1 # both wing ends closed with ribs (INTEGER) 0 – wing not closed with rib 1 – wing closed with tip rib 2 – wing closed with tip and root rib 1 # wing – fuselage intersection type (INTEGER) 1 – intersection (rib No. „0” – inside fuselage geometry rib No. „1” - outside fuselage geometry); 0 – no intersection (fuselage is fixed to the first rib of the wing, rib No. „0” rib is outside the fuselage geometry) 7 # number of the stringer which intersects the with wing leading edge point (this number is consistent with number in fuselage geometry file ,Fig. 5) 3 # number of sections defining wing (INTEGER) see description below: nac65006.prf # airfoil type for current wing section (“*.prf” file name) 5.20 # rib chord (REAL) 6.27 1.09 1.01 # rib leading edge coordinates (REAL) 0.00 1.00 0.00 # rib rotation angles X, Y, Z [deg] (REAL) This data can be omitted. Program will set it automatically. This procedure is not correct when first wing section is placed not on the models symmetry plane. section - 1 15
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 and 10: - lift force - drag force The aerod
Page 11 and 12: 1.2.3. Main computational subprogra
Page 13: File [name.f] - fuselage geometry -
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
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
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Fig. 86 - Models prepared with the
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