between the altitudes of 1000 ft. and 35000 ft. was calculated by integrating the equation 44 numerically using the corresponding values of RC for every altitude h: Eqn. (44)
Same calculation was repeated for different climb scenarios and results are presented in table 50. Based on the requirements
t (1000→35000) t (10000→35000) t (1000→10000) t (10000→20000)
9.02 min. 6.49 min. 2.25 min. 2.65 min.
defined by the RFP, the maximum climb rate at 36000 ft. isTable 50. time to climb for different scenarios calculated to be 112 ft./min. therefore verifying the service ceiling of approximately 36000 ft. The results of these calculations are presented in tables 51. Alt. α R/C CGR
PSpExPwr
36000ft. 7.53 deg. ft 112 min 0.03 3360.9
ft min
5000ft. -0.73 deg. ft 3587 min 0.22 ft 6.177 min
Table 51. Maximum ROC assumptions and result Fig. 70) ROC and γ vs. velocity for cruise altitude
3.8.3 Range and Endurance: One of the goals for this design is to create a vehicle having a range greater than 950 nautical miles exceeding the range requirement of the proposal both in constant altitude and constant speed cruise (800n.m.). To validate the fulfillment of this goal, the range and endurance calculations (in constant altitude or speed) based on the outlined method in Data Unit Volume II * were performed. For both analyses it is assumed that the aircraft uses a fuel tank with a capacity of 550 lbs. of fuel (Maximum fuel weight considered in detailed weight analysis), and will consume 460 lbs. of fuel during the cruise segment (84%). Fuel consumption properties were obtained from the released performance characteristics of the engine (J-1200) as a *
“Aquila Project Technical Data Unit, Vol. II” PP. 7-9
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