Aerodynamic coefficients for upward/downward deflections.

Table 3: Aerodynamic coefficients for upward/downward deflections.

Deflected

Surface

Aerodynamic Coefficient

δ_{i} = + 3 º

δ_{i} = - 3 º

α = 0 º

α = 3 º

α = 0.71789 º

α = 0 º

α = 3^{º}

α = 0.71789 º

i = 1

C_L1

C_D1

C_M1

0.01033

0.00396

0.00778

0.26590

0.00845

-0.05860

0.07149

0.00503

-0.00810

0.07780

0.00475

-0.02406

0.34000

0.01265

-0.09423

0.14054

0.00664

-0.04085

i = 2

C_L2

C_D2

C_M2

0.03384

0.00420

-0.00381

0.29079

0.00980

0.07087

0.09533

0.00554

-0.01986

0.50434

0.00429

-0.01255

0.31388

0.01092

-0.08119

0.11645

0.00588

-0.02897

i = 3

C_L3

C_D3

C_M3

0.01600

0.00441

0.00313

0.27080

0.00914

-0.06249

0.07702

0.00554

-0.01250

0.07240

0.00418

-0.01976

0.33707

0.01206

-0.09159

0.13573

0.00607

-0.03695

i = 4

C_L4

C_D4

C_M4

-0.00666

0.00518

0.01599

0.24644

0.00896

-0.04867

0.05390

0.00608

0.00052

0.09662

0.00375

-003357

0.36857

0.01364

-0.11080

0.16169

0.00612

-0.05205

i = 5

C_L5

C_D5

C_M5

0.02980

0.00481

0.00122

0.28626

0.01021

-0.06542

0.09117

0.00610

-0.01473

0.05870

0.00375

-0.01783

0.31943

0.01075

-0.08753

0.12109

0.00542

-0.03451

i = 0

C_L0

C_D0

C_M0

0.15977

0.00625

-0.00746

-0.09578

0.00644

0.05871

0.09862

0.00629

0.00837

0.49675

0.02343

-0.18107

0.19127

0.00473

-0.08014

0.42365

0.01896

-0.15692