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The source strength (constant for panel), can be defined (using definitions (10) , (11) and boundary condition of the closed body i/n=0) as follows: n V (16) It will result in a set of equation with the doublet strength as the unknown. To determine the doublet strength on the vortex wake, the Kutta-Joukowsky condition is used: TE = W = const (17) The doublet strength on the wake is equal to difference between doublet strength on the upper and lower surface close to the trailing edge. Using (17), the doublet strength on the wake can be obtained from formula: W = U - L (18) Fig. 3 – Relation between doublet strength on trailing edge and wake The formula (18) completes the set of equations (14). Only integrals (15) have to be determined. Effective method of determination of these integrals is shown in [6] and [7]. The solution of set (14) gives the potential distribution on the body surface. To obtain the pressure distribution, necessary to obtain the global aerodynamic coefficients, the velocity distribution must be found. It can be made by differentiation of the potential with respect to defined tangential coordinates. Next using Bernoulli’s theorem the pressure can be computed. The numerical differentiation in general case is not easy and can be the source of errors, especially in places, where the grid is not regular. 8
- lift force - drag force The aerodynamic loads can be obtained as follows: - pitching moment M y N P z P x N i1 N i1 piSi piSi n z i (19) n x p S x n z p S z ni x i1 i i i i (20) N i (21) i i i i1 The lateral load components (Py, Mx, Mz) can be computed in similar way if we define lateral components of airspeed. It must be underlined, that drag force obtained from (20) can be very inaccurate. The potential methods cannot give reliable results of aerodynamic drag. Package <strong>PANUKL</strong> 2002 computes the induced drag coefficient by use of Trefz method. 9
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: Fig. 1 - Approximation of the body
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
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Step 4 Right side of the object is
Page 61 and 62:
Important notes: What we should kno
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Main program options: Folder path f
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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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