First and second-order derivatives of aerodynamic coefficients.

Table 5: First and second-order derivatives of aerodynamic coefficients.

Surface

Coefficients

{C^{'}}_{X i}

{C^{″}}_{X i}

δ_i = -1.5°

δ_i = +1.5°

δ_i = 0°

δ_i = 0°

i = 1

C_L1

C_D1

C_M1

-0.01155

-0.000317

0.00548

-0.01146

-0.000220

0.00544

-0.011505

-0.0002685

0.00546

0.0000300

0.0000323

-0.0000133

i = 2

C_L2

C_D2

C_M2

-0.003523

-0.0000633

0.001520

-0.003527

-0.0000500

0.001517

-0.003525

-0.0000565

0.0015185

-0.00000133

0.00000443

-0.00000111

i = 3

C_L3

C_D3

C_M3

-0.00995

-0.000127

0.00418

-0.00962

-0.000050

0.00397

-0.009785

-0.0000885

0.004075

0.000110

0.0000257

-0.0000700

i = 4

C_L4

C_D4

C_M4

-0.00186

-0.000143

0.009213

-0.001732

0.000130

0.00831

-0.001796

-0.00000650

0.0087615

0.000427

0.0000910

-0.000302

i = 5

C_L5

C_D5

C_M5

-0.005070

0.0000900

0.003367

-0.004903

0.000137

0.003227

-0.0049865

0.0001135

0.003297

0.0000557

0.0000156

-0.0000467

i = 0

C_L0

C_D0

C_M0

-0.10682

-0.00552

0.04417

-0.00242

-0.00200

0.01092

-0.05320

-0.00321

0.027545

0.03480

0.00141

-0.01108