Create Balance Sheet, Profit and Loss Statement, Closing Entries, and Post Trial Balance

Accounts Payable 922,200

Accounts Receivable 723,300

Cash 141,100

Common Stock 454,900

Cost of Goods sold 9,501,400

Debt Investments, short-term 382,600

Equipment 921,000

Accumulated Depreciation--Equipment 36,000

Goodwill 202,700

Income Tax Expense 30,500

Income Tax Payable 7,200

Interest Expense 1,500

Inventory 1,636,500

Mortgage Payable 451,500

Notes Payable, due in 6 months 784,600

Notes Payable, due in 3 years 50,500

Retained Earnings, as of December 31, 2014 1,310,400

Salaries & Wages Expense 2,933,600

Sales Revenue Question 1). Answer :- Option d). Balance Sheet, Income Statement, Equity Holder...

1) What is finance? Define business finance. 2) Explain the types of finance. 3) Discuss the objectives of financial management. 4) Critically evaluate various approaches to the financial management. 5) Explain the scope of financial management. 6) Discuss the role of financial manager. 7) Explain the importance of financial management. 8) What is financial engineering 9) List three to four international undergraduate and graduate programs of financial engineeringAn aircraft flies at Mach 1.5 at 51000 ft (Pa=11 0KPa,To=216.7 K) propelled by a simple turbojet engine. The air enters the compressor and turbine at a rate of 20kg/s. (7=14,cp=1005J/{kg.Kj). a Find the stagnation temperature and pressure into the compressor, if the inlet is effectively isentropic. b. The engine compressor has a pressure ratio of 15 with an isentropic efficiency of 8516. Find the compressor work input. c. In the combustor the velocities are low (so the stagnation and static pressure are equal] with 596 pressure drop. At turbine entry the stagnation temperature is 1400 K and the turbine has an efficiency of 89%% and 65%% work output from turbine is used as compressor work input. Calculate the pressure ratio of the turbine and the thermal efficiency. d. If the final propelling nozzle is isentropic, find the velocity of the jet Subject on Gas Turbine EnginesThe schematic diagram of a typical gas turbine engine is illustrated in Figure Q3. The gas turbine engine draws air at 26-C at one bar and the maximum pressure limit of the cycle is 900 kPa. The effectiveness of the regenerator Is 80 percent and the efficiency of each compressor and turbine is 82 percent and 87 percent, respectively. This gas turbine engine used natural gas as a fuel for all heat input processes with a heating value of 53 MJ/kg burned al constant pressure in the combustion chamber of 90 percent efficiency and produces 1325-C maximum temperature. This gas turbine engine is designed to produces 85 KW of net power output. With the ald of T-s diagram based on the states in Figure Q4 and ulilizing cold air standard assumptions, determine; I) the specific heat input at combustion chamber, in) the total specific heat input al regenerator, fi) the thermal efficiency of the cycle, and iv) the cost of the natural gas in Ringgit Malaysia (RM) to run this engine continuously at constant load per day If the price of the natural gas is approximately 0.25 cent per gram. Regenerator Fuel 11) Combustion Chamber Compressor Compressor Turbine Turbine Turbine 1 1 10 Intercooler Reheater Beheater Fuel Fuel