185 lines
3.4 KiB
C++
185 lines
3.4 KiB
C++
// GENERAL
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maxSpeed = 450; // flight behavior arrays are dependable on this value
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acceleration = 300;
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landingAoa = 6*3.1415/180; // landing angle of attack in radians, for AI
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landingSpeed = 215; // for AI to approach the runawy, the plane should be stable at this speed
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stallSpeed = 190;
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stallWarningTreshold = 0.1;
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wheelSteeringSensitivity = 2.0; // steering authority of the nose wheel
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airBrake = 1;
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airBrakeFrictionCoef = 2.2;
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flaps = 1;
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flapsFrictionCoef = 0.32;
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gearsUpFrictionCoef = 0.6;
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airFrictionCoefs0[] = { 0.0, 0.0, 0.0 };
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airFrictionCoefs1[] = { 0.1, 0.5, 0.0066 };
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airFrictionCoefs2[] = { 0.001, 0.005, 0.000068};
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angleOfIndicence = -2*3.1415/180; // difference between forward and airfold chord line in radians
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envelope[] =
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{
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0.0, // 0
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0.05, // 50
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0.2, // 100
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0.46, // 150
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0.82, // 200
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1.28, // 250
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1.84, // 300
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2.4, // 350
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2.88, // 400
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3.65, // 450
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4.5, // 500
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5.45, // 550
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6.48, // 600
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7.61, // 650
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8.1, // 700
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8.3, // 750
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8.4, // 800
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8.3, // 850
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8.0, // 900
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7.6, // 950
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7.0 // 1000
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};
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// THRUST
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altNoForce = 13000;
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altFullForce = 2000;
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thrustCoef[] =
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{ // fSpeed = maxI * speedRel; speedRel = speed / (maxSpeed * 1.5f); maxI = _thrustCoef.Size() - 1;
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1.42, // 0
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1.38, // 75
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1.34, // 150
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1.30, // 225
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1.25, // 300
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1.20, // 375
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1.19, // 450
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1.18, // 525
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1.17, // 600
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1.17, // 675
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1.16, // 750
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1.16, // 825
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0.1, // 900
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0.0, // 975
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0.0, // 1050
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0.0, // 1125
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0.0 // 1200
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};
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// CONTROL SURFACES
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aileronSensitivity = 0.5;
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/* ---------------------------------
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aileronCoef[] =
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{
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0.0, // 0
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0.11, // 75
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0.45, // 150
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0.81, // 225
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1.1, // 300
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1.15, // 375
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1.2, // 450
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1.25, // 525
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1.3, // 600
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1.35, // 675
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1.4, // 750
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1.43, // 825
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1.45, // 900
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1.47, // 975
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1.4, // 1050
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1.2, // 1125
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0.8 // 1200
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};
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----------------------------- */
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aileronCoef[]={0,0.5,0.89999998,1,1.05,1.1,1.12};
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elevatorSensitivity = 1.6;
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elevatorCoef[] =
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{
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0.0, // 0
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0.14, // 75
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0.54, // 150
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0.62, // 225
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0.58, // 300
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0.56, // 375
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0.54, // 450
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0.52, // 525
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0.48, // 600
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0.43, // 675
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0.38, // 750
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0.35, // 825
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0.3, // 900
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0.25, // 975
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0.2, // 1050
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0.15, // 1125
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0.1 // 1200
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};
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rudderInfluence = 0.8660; // Basic angle (cos angle) of the rudder extent
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rudderCoef[] = // default value is fabs(speed.Z())*InvSqrt(Square(speed.X())+Square(speed.Z()));
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{
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0.0, // 0
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0.8, // 120
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2.0, // 240
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2.2, // 360
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2.3, // 480
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2.4, // 600
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2.3, // 720
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2.2, // 840
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2.1, // 960
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2.0, // 1080
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1.2 // 1200
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};
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// CONTROLS - sensitivity/speed in which control surface reaches its maximum extent
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aileronControlsSensitivityCoef = 3.6; // default value is 4
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elevatorControlsSensitivityCoef = 3.4; // default value is 4
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rudderControlsSensitivityCoef = 3.8; // default value is 4
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// FORCES - how good the airplane changes the flight vector or alignes with it
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draconicForceXCoef = 8.0; //7.5
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draconicForceYCoef = 1.4; //1
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draconicForceZCoef = 1.0; //1
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draconicTorqueXCoef[] =
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{
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4.8, // 0
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5.0, // 120
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5.5, // 240
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6.2, // 360
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7.0, // 480
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7.7, // 600
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9.4, // 720
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11.1, // 840
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12.0, // 960
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14.0, // 1080
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15.0 // 1200
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};
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draconicTorqueYCoef[] =
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{
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12.0, // 0
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10.0, // 75
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6.0, // 150
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2.0, // 225
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0.2, // 300
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0.0, // 375
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0.0, // 450
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0.0, // 525
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0.0, // 600
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0.0, // 675
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0.0, // 750
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0.0, // 825
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0.0, // 900
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0.0, // 975
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0.0, // 1050
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0.0, // 1125
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0.0 // 1200
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};
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// VTOL - behavior while vectoring
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// VTOLYawInfluence = 1.0;
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// VTOLPitchInfluence = 1.0;
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// VTOLRollInfluence = 1.0;
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