Master Thesis - Dechamps - Implementation of the linear part

Description

This MR adds the linear part of fpm, the symmetry option for symmetric wings and two additional test cases.
This version of fpm requires waves-v2.1.1.

Changes

• Add computations of the surface aerodynamic influence coefficients
• Add computation of the velocity
• Update the functions computing the density, the Mach number and the pressure coefficient
• Add the symmetry support
• Add two new test cases: Onera M6 wing and Agard 445 wing

Tests

• msys2 (gcc 10.2, python 3.9.7)

fpm/models/agard445.geo

+/* AGARD 445 wing */
+
+// Mesh parameters
+// domain and mesh
+DefineConstant[ wNc = { 50, Name "Number of panel along chord" }
+                wNs= { 10, Name "Number of panel along span" }
+                bC = { 0.05, Name "Progression along chord" }
+                pS = { 1.0, Name "Progression along span" } ];
+
+//// GEOMETRY
+/// Points
+// Airfoil 1: agard445, 51 points 
+Point(1) = {0.559000,0.000000,0.000000};
+Point(2) = {0.531050,0.000000,0.001398};
+Point(3) = {0.503100,0.000000,0.002739};
+Point(4) = {0.475150,0.000000,0.004075};
+Point(5) = {0.447200,0.000000,0.005406};
+Point(6) = {0.419250,0.000000,0.006680};
+Point(7) = {0.391300,0.000000,0.007837};
+Point(8) = {0.363350,0.000000,0.008866};
+Point(9) = {0.335400,0.000000,0.009743};
+Point(10) = {0.307450,0.000000,0.010442};
+Point(11) = {0.279500,0.000000,0.010923};
+Point(12) = {0.251550,0.000000,0.011158};
+Point(13) = {0.223600,0.000000,0.011163};
+Point(14) = {0.195650,0.000000,0.010968};
+Point(15) = {0.167700,0.000000,0.010576};
+Point(16) = {0.139750,0.000000,0.009995};
+Point(17) = {0.111800,0.000000,0.009196};
+Point(18) = {0.083850,0.000000,0.008156};
+Point(19) = {0.055900,0.000000,0.006781};
+Point(20) = {0.041925,0.000000,0.005920};
+Point(21) = {0.027950,0.000000,0.004891};
+Point(22) = {0.013975,0.000000,0.003617};
+Point(23) = {0.006988,0.000000,0.002622};
+Point(24) = {0.004193,0.000000,0.002057};
+Point(25) = {0.002795,0.000000,0.001699};
+Point(26) = {0.000000,0.000000,0.000000};
+Point(27) = {0.002795,0.000000,-0.001699};
+Point(28) = {0.004193,0.000000,-0.002057};
+Point(29) = {0.006988,0.000000,-0.002622};
+Point(30) = {0.013975,0.000000,-0.003617};
+Point(31) = {0.027950,0.000000,-0.004891};
+Point(32) = {0.041925,0.000000,-0.005920};
+Point(33) = {0.055900,0.000000,-0.006781};
+Point(34) = {0.083850,0.000000,-0.008156};
+Point(35) = {0.111800,0.000000,-0.009196};
+Point(36) = {0.139750,0.000000,-0.009995};
+Point(37) = {0.167700,0.000000,-0.010576};
+Point(38) = {0.195650,0.000000,-0.010968};
+Point(39) = {0.223600,0.000000,-0.011163};
+Point(40) = {0.251550,0.000000,-0.011158};
+Point(41) = {0.279500,0.000000,-0.010923};
+Point(42) = {0.307450,0.000000,-0.010442};
+Point(43) = {0.335400,0.000000,-0.009743};
+Point(44) = {0.363350,0.000000,-0.008866};
+Point(45) = {0.391300,0.000000,-0.007837};
+Point(46) = {0.419250,0.000000,-0.006680};
+Point(47) = {0.447200,0.000000,-0.005406};
+Point(48) = {0.475150,0.000000,-0.004075};
+Point(49) = {0.503100,0.000000,-0.002739};
+Point(50) = {0.531050,0.000000,-0.001398};
+// Airfoil 2: agard445, 51 points 
+Point(52) = {1.178128,0.762000,0.000000};
+Point(53) = {1.159709,0.762000,0.000921};
+Point(54) = {1.141290,0.762000,0.001805};
+Point(55) = {1.122870,0.762000,0.002685};
+Point(56) = {1.104451,0.762000,0.003562};
+Point(57) = {1.086032,0.762000,0.004402};
+Point(58) = {1.067613,0.762000,0.005165};
+Point(59) = {1.049194,0.762000,0.005843};
+Point(60) = {1.030775,0.762000,0.006421};
+Point(61) = {1.012356,0.762000,0.006881};
+Point(62) = {0.993937,0.762000,0.007198};
+Point(63) = {0.975518,0.762000,0.007353};
+Point(64) = {0.957099,0.762000,0.007357};
+Point(65) = {0.938680,0.762000,0.007228};
+Point(66) = {0.920261,0.762000,0.006970};
+Point(67) = {0.901842,0.762000,0.006587};
+Point(68) = {0.883423,0.762000,0.006060};
+Point(69) = {0.865004,0.762000,0.005375};
+Point(70) = {0.846585,0.762000,0.004468};
+Point(71) = {0.837375,0.762000,0.003901};
+Point(72) = {0.828166,0.762000,0.003223};
+Point(73) = {0.818956,0.762000,0.002383};
+Point(74) = {0.814351,0.762000,0.001728};
+Point(75) = {0.812509,0.762000,0.001356};
+Point(76) = {0.811589,0.762000,0.001120};
+Point(77) = {0.809747,0.762000,0.000000};
+Point(78) = {0.811589,0.762000,-0.001120};
+Point(79) = {0.812509,0.762000,-0.001356};
+Point(80) = {0.814351,0.762000,-0.001728};
+Point(81) = {0.818956,0.762000,-0.002383};
+Point(82) = {0.828166,0.762000,-0.003223};
+Point(83) = {0.837375,0.762000,-0.003901};
+Point(84) = {0.846585,0.762000,-0.004468};
+Point(85) = {0.865004,0.762000,-0.005375};
+Point(86) = {0.883423,0.762000,-0.006060};
+Point(87) = {0.901842,0.762000,-0.006587};
+Point(88) = {0.920261,0.762000,-0.006970};
+Point(89) = {0.938680,0.762000,-0.007228};
+Point(90) = {0.957099,0.762000,-0.007357};
+Point(91) = {0.975518,0.762000,-0.007353};
+Point(92) = {0.993937,0.762000,-0.007198};
+Point(93) = {1.012356,0.762000,-0.006881};
+Point(94) = {1.030775,0.762000,-0.006421};
+Point(95) = {1.049194,0.762000,-0.005843};
+Point(96) = {1.067613,0.762000,-0.005165};
+Point(97) = {1.086032,0.762000,-0.004402};
+Point(98) = {1.104451,0.762000,-0.003562};
+Point(99) = {1.122870,0.762000,-0.002685};
+Point(100) = {1.141290,0.762000,-0.001805};
+Point(101) = {1.159709,0.762000,-0.000921};
+
+/// Lines
+// Airfoil 1:
+Spline(1) = {1:26};
+Spline(2) = {26:50,1};
+// Airfoil 2:
+Spline(3) = {52:77};
+Spline(4) = {77:101,52};
+// Airfoil 1 to airfoil 2:
+Line(61) = {1,52};
+Line(62) = {26,77};
+
+
+/// Line loops & Surfaces
+// Wing 1:
+Line Loop(11) = {1,62,-3,-61};
+Line Loop(12) = {2,61,-4,-62};
+Surface(11) = {-11};
+Surface(12) = {-12};
+
+//// MESH
+Transfinite Line{1,2,3,4} = wNc+ 1 Using Bump bC;
+Transfinite Line{61,62} = wNs + 1 Using Progression pS;
+Transfinite Surface{11,12};
+Recombine Surface{11,12};
+
+//// PHYSICAL GROUPS
+// Trailing edge
+Physical Line("wTe") = {61};
+// Wing:
+Physical Surface("wing") = {11,12};