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3.1.5. XFOIL menu description Fig. 36 – Configuration window – Correct Neighbours Fig. 37 – XFOIL menu In XFOIL menu user can find functions which can help to analyze aerodynamic airfoils (used in wing geometry definition) using XFOIL program. To use it wisely user must have basic knowledge about XFOIL program. Available options in XFOIL menu) Function Description Interactive mode Interactive mode for stored wing section geometry Click to run external XFOIL program (must be installed [2.1]). Standard program window will appear (Fig. 38), XFOIL is ready to work. Click to run XFOIL for specified *.dat file (Fig. 38). *.dat file contains coordinates of an airfoil to be analyzed. 42
Fig. 38 – External XFOIL program window & *.dat file selection window Function Description Polar calculation Open XFOIL polar Computing basic aerodynamic characteristics for an airfoil: CL-lift, CD-drag, CM-moment, versus angle of attack and Reynolds & Mach number. (airfoil geometry saved to *.dat file). Aerodynamic characteristics are computed in XFOIL external program. Results saved to *.txt file (Fig. 41). Load file from disk with saved aerodynamic characteristics (Fig. 41). When *.txt file is loaded, functions below turn active: Show Drag polar Show drag CD polar, Fig. 42. Show Lift coefficient Show lift coefficient CL graph, Fig. 42. Show Moment coefficient Show moment coefficient CM graph, Fig. 42. 43
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: Downwash calculation: Number of mes
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
Page 71 and 72: Fig. 86 - Models prepared with the

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