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1.1.4. Computational method Computational method strongly depends on the way of aircraft body modeling. The model defined in chapter 1.1.3 concerns only flow and doesn’t define the object. Generally two methods are in use. In the first method the body of aircraft is modeled using thin surfaces. The second method uses three dimensional model of the aircraft body. <strong>PANUKL</strong> 2002 package bases on the low order panel method, where the Dirichlet problem is solved (Hess method [7]). The quadrangle panels are used. The flat vortex wake, parallel to the free stream velocity or parallel to chord is assumed. The base of the method is solution of the Laplace equation for the full velocity potential. The velocity potential can be written in form [6]: 1 1 1 4 n r 4 2 0; (7) x, y, z dS dS BODY WAKE Assuming the following boundary conditions: - internal Dirichlet boundary condition on the body surface: where: 1 4 BODY 1 1 dS n r 4 WAKE BODY BODY 1 r 1 dS 0 r doublet strength: = - ( - i ), (10) source strength: = /n. (11) - Kutta-Joukowsky conditions on the trailing edge: - on the vortex wake: p( x, y) TE 0 (12) ( x, y) 0; x (8) (9) (13) 6
Fig. 1 – Approximation of the body surface by panel elements and assuming, that the velocity potential inside the body i is equal to velocity potential in infinity the integral equation is derived in form (9). The approximation of the aircraft body surface by flat panels allows to approximate the equation (9) by system of linear algebraic equations with unknown doublet strength (constant for panel): N N N w Ck k + Cl l + Bk k = 0 (14) k=1 l=1 where Ck , Cl and Bk denote influence coefficients: C 1 1 k=1 k dSk 4 n ; Bk dSk r S1234 k 4 r S1234 k N – numbers of panels on the aircraft surface; NW – number of panels on the wake; S1234 – area of the k-th panel; Fig. 2 – Influence of K-th panel on point P 1 1 (15) 7
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: 1.1.2. Introduction The develop of
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
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4.2. Creation of complex computatio
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Step 4 Right side of the object is
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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
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Remember: don’t insert DATUM PLAN
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In some fuselage areas you will hav
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Fig. 86 - Models prepared with the
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