Climb: Difference between revisions
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Rate-of-climb (ROC) is identically the specific excess power. Excess power is the difference between how much thrust power the propeller is putting into the air and how much power it takes to overcome drag. Specific excess power is the excess power divided by the aircraft's weight. Because ROC is related to ''excess'' power, doubling or halving the thrust power does not mean the rate-of-climb or descent is doubled or halved. A good example is a light twin such as an [http://en.wikipedia.org/wiki/Piper_Aztec Apache]. If an Apache loses an engine (thrust power reduced by half), the remaining engine usually does not have enough power to even sustain level flight. | Rate-of-climb (ROC) is identically the specific excess power. Excess power is the difference between how much thrust power the propeller is putting into the air and how much power it takes to overcome drag. Specific excess power is the excess power divided by the aircraft's weight. Because ROC is related to ''excess'' power, doubling or halving the thrust power does not mean the rate-of-climb or descent is doubled or halved. A good example is a light twin such as an [http://en.wikipedia.org/wiki/Piper_Aztec Apache]. If an Apache loses an engine (thrust power reduced by half), the remaining engine usually does not have enough power to even sustain level flight. | ||
Using the numbers quoted in the Pilot's Operating Handbook, the rate-of-climb at a gross weight of 2200 lbs is | Using the numbers quoted in the Pilot's Operating Handbook for a Cheetah, the rate-of-climb at a gross weight of 2200 lbs is 660 ft/min. By definition, the excess power of a [http://en.wikipedia.org/wiki/Grumman_American_AA-5#AA-5A_Cheetah Cheetah] in the original factory configuration is 44 HP. Therefore, even small amount of additional brake power or improvements in propeller efficiency will have a large impact on excess power and, therefore, rate-of-climb. | ||
== Effect of the High Compression STC, PowerFlow Exhaust, and Sensenich Propeller == | == Effect of the High Compression STC, PowerFlow Exhaust, and Sensenich Propeller == | ||
The effect of these performance enhancers is a common topic on the [http://grumman.net Grumman Gang]. Until estimated performance data is available for the PowerFlow exhaust and Sensenich propeller, only the improvement due to the High Compression STC is discussed. Data approximating the performance impact due to the High Compression STC is discussed in [[Basic Engine and Propeller Performance]] and will be used here. | |||
The improved rate-of-climb can be computed from the original rate-of-climb as follows: new rate-of-climb = old rate-of-climb + (new - old thrust power / aircraft weight). Recognizing the data in [[Basic Engine and Propeller Performance]] is somewhat off due to the generic propeller curves and handpicking points off of those curves, at 80 KIAS the old and new thrust is 458 lbs and 498 lbs (an increase of 8%), respectively. When converted to thrust power at 80 KIAS, this results in a net excess horsepower increase of 9.7 HP, which translates into a net increase in rate-of-climb of approximately 22%, from 660 ft/min to 805 ft/min at Cheetah gross weight. Note that this is from the High Compression STC alone without any propeller or exhaust improvements. But the shocker to most is that a 22% increase in rate-of-climb can be obtained from a 6.7% increase in maximum rate engine power. | |||
Revision as of 17:06, 21 January 2008
Factors Influencing Climb Performance
Rate-of-climb (ROC) is identically the specific excess power. Excess power is the difference between how much thrust power the propeller is putting into the air and how much power it takes to overcome drag. Specific excess power is the excess power divided by the aircraft's weight. Because ROC is related to excess power, doubling or halving the thrust power does not mean the rate-of-climb or descent is doubled or halved. A good example is a light twin such as an Apache. If an Apache loses an engine (thrust power reduced by half), the remaining engine usually does not have enough power to even sustain level flight.
Using the numbers quoted in the Pilot's Operating Handbook for a Cheetah, the rate-of-climb at a gross weight of 2200 lbs is 660 ft/min. By definition, the excess power of a Cheetah in the original factory configuration is 44 HP. Therefore, even small amount of additional brake power or improvements in propeller efficiency will have a large impact on excess power and, therefore, rate-of-climb.
Effect of the High Compression STC, PowerFlow Exhaust, and Sensenich Propeller
The effect of these performance enhancers is a common topic on the Grumman Gang. Until estimated performance data is available for the PowerFlow exhaust and Sensenich propeller, only the improvement due to the High Compression STC is discussed. Data approximating the performance impact due to the High Compression STC is discussed in Basic Engine and Propeller Performance and will be used here.
The improved rate-of-climb can be computed from the original rate-of-climb as follows: new rate-of-climb = old rate-of-climb + (new - old thrust power / aircraft weight). Recognizing the data in Basic Engine and Propeller Performance is somewhat off due to the generic propeller curves and handpicking points off of those curves, at 80 KIAS the old and new thrust is 458 lbs and 498 lbs (an increase of 8%), respectively. When converted to thrust power at 80 KIAS, this results in a net excess horsepower increase of 9.7 HP, which translates into a net increase in rate-of-climb of approximately 22%, from 660 ft/min to 805 ft/min at Cheetah gross weight. Note that this is from the High Compression STC alone without any propeller or exhaust improvements. But the shocker to most is that a 22% increase in rate-of-climb can be obtained from a 6.7% increase in maximum rate engine power.
