AIRPLANE DATA

The following samples of airplane data (Figures A.3.1 to A.3.20 and Table A.3.1) are taken from Aircraft Handling Qualities Data, by Robert K. Heffley and Wayne F. Jewell, NASACR-2144, December 1972. The figures include:

• Flight envelope.

• CL and CD as a function of M and altitude.

• Weight and moments of inertia.

• Three-view sketches to scale.

In addition, stability derivatives are tabulated for the Convair 880… The following definitions apply to notations on the sketches.

0.25c F. S. 205.5

F. S. = fuselage station = inches aft of reference transverse plane near nose.

W. L. = waterline = inches above horizontal reference plane.

B. L. = buttline = inches to right of vertical plane of symmetry.

Nominal Configuration

1.4 Vs

W= 11,8001b eg at 0.260c, W. L. 100 Ix = 12,700 slug-ft’

Iy = 20,700 slug-ft’

Iz = 32,000 slug-ft‘

/„ = 480 slug-ft2

Figure A.3.4 X-15; a general arrangement.

Nominal Configuration

Zero fuel Lower ventral on Speed brakes retracted W= 15,5601b eg at 0.22c ix = 3650 slug-ft2 I, = 80,000 slug-ft2 Iz = 82,000 slug-ft2 Іхг = 590 slug-ft2

1.0

0.5

0.2

0.1

0.05

0.02

0.01

Figure A.3.6 X-15; 15,560 lb.

S = 6297.8 ft2 b = 105 ft c = 78.53 ft

^—————– r-TT-n———–

00 00 00 О

Figure A.3.10 XB-70A; a general arrangement.

Nominal Configuration

W = 300,000 lb eg at 0.235 c lx = 1.45 x 106 slug-ft2 /,. = 16 x 106 slug-ft2 U = 17.2 X 106 slug-ft2 /„ = -0.6 x 106 slug-ft2

________ SL

——— 20,000 ft

——– 40,000 ft

——— 60,000- ft

Table A.3.1 CV-880 M Longitudinal Nondimensional Stability Derivatives

Flight condition

1

2

3

4

5

6

7

Configuration

L

PA

Speed

134 KTAS

165 KTAS

0.6M

0.86M

0.7M

0.8M

0.86М

Altitude

SL

SL

23 К

23 К

35 К

35 К

35 К

<*o (deg)

5.2

4.3

5.3

2.8

8.3

4.7

4.0

CL

1.03

0.68

0.36

0.175

0.454

0.347

0.301

CD

0.154

0.080

0.022

0.019

0.025

0.024

0.023

Си, (1/rad)

4.66

4.52

4.28

4.41

4.62

4.8

4.9

CD, (1/rad)

0.43

0.27

0.14

0.07

0.18

0.15

0.13

Cm„ (1/rad)

-0.381

-0.903

-0.522

-0.572

-0.568

-0.65

-0.74

CL, (1/rad)

2.7

2.7

2.44

2.5

2.75

2.75

2.9

CLe (1/rad)

7.92

7.72

6.76

6.37

7.51

7.5

7.62

Cm, (1/rad)

-4.17

-4.13

-4.16

-4.66

-4.4

-4.5

-4.6

C„a (1/rad)

-12.2

-12.1

-11.5

-11.8

-12.0

-12.0

-12.0

CLs (1/rad)

0.22

0.213

0.193

0.141

0.203

0.190

0.180

Cmh (1/rad)

-0.657

-0.637

-0.586

-0.438

-0.618

-0.57

-0.532

Chs (1/rad)

-10.326

-0.328

-0.336

-0.278

-0.342

-0.31

-0.285

Cl, (1/rad)

0.055

0.0532

0.482

0.0352

0.0508

0.047

0.0450

Cm„; (1/rad)

-0.164

-0.159

-0.146

-0.11

-0.155

-0.14

-0.134

Ch,’ (1/rad)

-0.287

-0.285

-0.297

-0.343

-0.312

-0.335

-0.352

S = 160 ft2 b= 13.6 ft T= 21.17 ft

Nominal Configuration

Zero fuel (burnout)

Gear up

Transonic or subsonic configuration, depending on flight condition W = 6466 lb

eg at 0.517c, W. L. Ix = 1353 slug-ft2 Iy = 6413 slug-ft2 J2 = 7407 slug-ft2 /„ = 399 slug-ft2

Figure A.3.19 HL-10; flight envelope; nominal envelope extremes.

Configuration

Speed Brakes

Elevon Flaps

Tip-Fin Flaps

Subsonic

Zero

Zero

Zero

Transonic

30°

30.5°/32.5°

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