For the C172D flying at sea level (density = 0.002377 slug/ft^3) with V∞= 95 knots (160ft/s), compute:
Find :
Lift coefficient
Drag coefficient
(L/D) ratio
Thrust Required(TR)
Power Required(PR)
at IAS 50ft/s
I found the CL, CD and L/D but I need help finding the TR and
PR
| Wingspan | 35.8 ft | |
| Wing area | 174 ft22 | |
| Normal gross weight | 2300 lb | |
| Fuel Capacity | 38 Gal. of Aviation Gasoline | |
| Power Plant | One 160 hp piston engine at sea level | |
| Specific fuel consumption | 0.45 lb/(hp)(h) | |
| Parasite Drag Coefficient, | 0.025 | |
| Oswald Efficiency Factor, | 0.8 | |
| Propeller Efficiency Factor, |
0.8 |


For the C172D flying at sea level (density = 0.002377 slug/ft^3) with V∞= 95 knots (160ft/s), com...
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