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Tham khảo tài liệu 'thiết kế kỹ thuật máy bay chiến đấu episode 2 part 2', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | POWER FOR FLIGHT 245 Fig. 6.12 Pitts S-2A two seater in single-seat configuration drawing from Underwood John w. Acrobats in the Sky Heritage Press Box 167 Glendale California 91209. Author s figures added . 246 THE DESIGN OF THE AEROPLANE w s Ks 2 50 00 50 o 5 10 5 2o 25 So loQ.diio IL fl Fig. 6.13a and b Typical combinations of loadings needed in project design a. Wing and power loading b. Average power per unit gross wing area. When all other aspects of aircraft configuration and geometry are fixed rate of climb varies inversely with weight for a given power. This is useful when working out flight test results in which the rate of climb is know for one weight when the aircraft has been flown at another. As long as the difference between the weights is not large and the aeroplane has been flown at the correct lift drag ratio rate of climb at lighter weight rate of climb at heavier weight heavier weight lighter weight 6-37 Power and thrust loading w p and W F are useful indications of merit for comparing different aeroplanes. Their reciprocals p IFand F w when multiplied by weight tell how much power or thrust is needed to achieve a given rate of climb. But the approach made here is crude in the sense that we have not dealt with other important factors like lift drag ratio which affect induced drag. Aeroplanes with long wings climb better and achieve higher service ceilings than those with short forgiven power and wing loadings see fig. 6.14c and d . Supercharging of various kinds maintains sea level power to higher altitudes inhibiting the decrease in rate of climb with altitude experienced by aeroplanes powered with normally aspirated engines. POWER FOR FLIGHT 247 w s R- 3 IS lẻ 14 5 o i ool o 140 I2o too So Ế 0 40 Zo o IO 2o ê o 4o So p s klV hA o locxciii w s Fig. .