Textbook Assigned Problems – Chapter 2:

2.1           Density, r = 1.41 kg/m3
Specific Volume, v = 0.71 m3/kg

2.2           N/A

2.3           Weight of air, w = 183 pounds

2.4           Density of air at the colder temperature, r = 0.00274 slug/ft3
Percentage change in air weight, D = 15.6% increase.

2.5           Air pressure, p = 47,290 lb/ft2 = 22.3 atmospheres

2.6           N/A

2.7           Density, r = 0.225 kg/m3.

2.8           N/A

2.9           N/A

2.10        Minimum velocity occurs at q = 0º and q = 180 º, Vmin = 0 miles/hour.
Maximum velocity occurs at q = 90º, Vmax = 127.5 miles/hour.

Textbook Assigned Problems – Chapter 3:

3.1           Pressure @18Km, p = 7.53 x 103 N/m2
Density @18Km, r = 0.121 kg/m3
Temperature @18Km, T = 216.66 K

3.2           Pressure Altitude = 10 km (From Appendix A)
Density, r = 0.419 kg/m3 so:
Density Altitude = 9.88 km

3.3           Pressure @35 Kft, p = 499 Lb/ft2

3.4           Temperature, T = 378º R

3.5           N/A

3.6           N/A

3.7           Altitude, h = 17,358 m = 17.358 km

3.8           N/A

3.9           Elevator speed, dh/dt = 84.1 m/min

3.10        Pressure Altitude, PA = 33,737 feet
Density Altitude, DA = 33,156 feet

Textbook Assigned Problems – Chapter 4:

4.1           Water flow velocity at exit, V2 = 1.25 feet/sec

4.2           Pressure Difference, DP = 22.7 Lb/ft2

4.3           Pressure on wing, P2 = 6.95x104 N/m2

4.4           Airplane velocity, V = 67 feet/sec = 46 miles/hour

4.5           Velocity @ Throat, V = 102.22 meters/sec

4.6           Velocity on win, V2 = 216.8 feet/sec

4.7           Thru 4.14 N/A

4.15        Mach Number of 747, M = 0.847

4.16        Thru 4.19 N/A

4.20        Total Pressure, P0 = 2172 Lb/ft2

4.21        True Airspeed, VTAS = 292 feet/sec
Equivalent Airspeed, VEAS = 256 ft/sec

4.22        True Airspeed, VTAS = 56 meters/sec

4.23        Total Pressure, P0 = 1.48x105 N/m2

4.24        Thru 4.38 N/A

4.39        Equivalent Airspeed, VEAS = 535.8 feet/sec

Textbook Assigned Problems – Chapter 5:

5.1         N/A

5.2         Lift per unit span, L = 23.9 Lb/Foot
Drag per unit span, D = 0.25 Lb/Foot
Moment per unit span, M = -2.68 Ft-Lb/Foot

5.3         Lift per unit span, L = 301 N/Meter
Drag per unit span, D = 3.07 N/Meter
Moment per unit span, M = -1.1 N-Meter/Meter

5.4         Angle of Attack, a = 2 Degrees

5.5         Reference Area, S = 2 Ft2

5.6         Maximum Lift-to-Drag ratio, (L/D)max @ 112

5.7         Pressure Coefficient, Cp = -3.91

5.8         Pressure Coefficient, Cp = -0.27

5.9         Pressure Coefficient, Cp = -0.485