First- and second-order central differences of aerodynamic coefficients.

Table 4: First- and second-order central differences of aerodynamic coefficients.

AOA: $α = 0.71789 º$

C_{X i}

\nabla C_{X i}

\nabla^{2} C_{X i}

Surface

Coefficients

d _i = -3°

d _i = 0°

d _i = +3°

d _i = -1.5°

d _i = +1.5°

d _i = 0°

i = 1

C _L1

C _D1

C _M1

0.14054

0.00664

-0.04085

0.10588

0.00569

-0.02441

0.07149

0.00503

-0.00810

-0.03466

-0.000950

0.01644

-0.03439

-0.000660

0.01631

0.000270

0.000290

-0.00013

i = 2

C _L2

C _D2

C _M2

0.11645

0.00588

-0.02897

0.10588

0.00569

-0.02441

0.09533

0.00554

-0.01986

-0.01057

-0.00019

0.00456

-0.101058

-0.00015

0.00455

-0.00001

0.00004

-0.00001

i = 3

C _L3

C _D3

C _M3

0.13573

0.00607

-0.03695

0.10588

0.00569

-0.02441

0.07702

0.00554

-0.01250

-0.02985

-0.00038

0.01254

-0.2886

-0.00015

0.01191

0.00099

0.00023

-0.00063

i = 4

C _L4

C _D4

C _M4

0.16169

0.00612

-0.05205

0.10588

0.00569

-0.02441

0.05390

0.00608

0.00052

-0.00558

-0.0043

0.02764

-0.05198

0.00039

0.02493

-0.04640

0.00082

-0.00271

i = 5

C _L5

C _D5

C _M5

0.12109

0.00542

-0.03451

0.10588

0.00569

-0.02441

0.09117

0.00610

-0.01473

-0.01521

0.00027

0.01010

-0.01471

0.00041

0.00968

0.00050

0.00014

-0.00041

i = 0

C _L0

C _D0

C _M0

0.42635

0.01896

-0.15692

0.10588

0.00569

-0.02441

0.09862

0.00629

0.00837

-0.32047

-0.01327

0.13251

-0.00726

-0.000600

0.03278

0.31321

0.01267

-0.09973