PANUKL Help - ITLiMS
PANUKL Help - ITLiMS PANUKL Help - ITLiMS
Fig. 39 – Polar calculations setup window During XFOIL aerodynamic computations user must check if results converge. Otherwise obtained results can have no physical sense. For more information go to XFOIL manual. Fig. 40 – XFOIL window – aerodynamic coefficients computations for an airfoil 44
Fig. 41 – Selecting result file with aerodynamic characteristics for an airfoil When *.txt file is loaded: Show Drag polar, Show Lift coefficient, Show Moment coefficient functions turn active. Fig. 42 – Example results CL, CD, CM versus Angle of Attack 45
- 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 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: Fig. 38 - External XFOIL program wi
- 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
- Page 71 and 72: Fig. 86 - Models prepared with the
Fig. 39 – Polar calculations setup window<br />
During XFOIL aerodynamic computations user must check if results converge.<br />
Otherwise obtained results can have no physical sense. For more information go to XFOIL manual.<br />
Fig. 40 – XFOIL window – aerodynamic coefficients computations for an airfoil<br />
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