如何群眾性的航空模型運(yùn)動(dòng)得到蓬勃發(fā)展,運(yùn)動(dòng)水平迅速提高。那么，下文是由大型航天模型廠家為大家提供的航空模型知識(shí)講解，歡迎大家來(lái)看。

How to make the mass aviation model movement flourish and improve the sports level rapidly. Then, the following is an explanation of aviation model knowledge provided by large aerospace model manufacturers. Welcome to see it.

1、升力和阻力

1. Lift and drag

飛機(jī)和模型飛機(jī)之所以能飛起來(lái)，是因?yàn)闄C(jī)翼的升力克服了重力。機(jī)翼的升力是機(jī)翼上下空氣壓力差形成的。當(dāng)模型在空中飛行時(shí)，機(jī)翼上表面的空氣流速加快，壓強(qiáng)減小;機(jī)翼下表面的空氣流速減慢壓強(qiáng)加大(伯努利定律)。這是造成機(jī)翼上下壓力差的原因。

The reason why aircraft and model aircraft can fly is that the lift of wings overcomes gravity. The lift of the wing is caused by the difference between the upper and lower air pressure of the wing. When the model flies in the air, the air velocity on the upper surface of the wing increases and the pressure decreases; The air velocity on the lower surface of the wing slows down and the pressure increases (Bernoulli's law). This is the cause of the pressure difference between the upper and lower wings.

機(jī)翼上下流速變化的原因有兩個(gè)：a、不對(duì)稱(chēng)的翼型;b、機(jī)翼和相對(duì)氣流有迎角。翼型是機(jī)翼剖面的形狀。機(jī)翼剖面多為不對(duì)稱(chēng)形，如下弧平直上弧向上彎曲(平凸型)和上下弧都向上彎曲(凹凸型)。對(duì)稱(chēng)翼型則須有一定的迎角才產(chǎn)生升力。

There are two reasons for the variation of the upper and lower velocity of the wing: a. asymmetric airfoil; b. The wing has an angle of attack with the relative airflow. An airfoil is the shape of an airfoil section. The airfoil profile is mostly asymmetric, with the following straight arcs curving upward (flat convex type) and the upper and lower arcs curving upward (concave convex type). Symmetrical airfoils must have a certain angle of attack to generate lift.

升力的大小主要取決于四個(gè)因素：a、升力與機(jī)翼面積成正比;b、升力和飛機(jī)速度的平方成正比。同樣條件下，飛行速度越快升力越大;c、升力與翼型有關(guān)，通常不對(duì)稱(chēng)翼型機(jī)翼的升力較大;d、升力與迎角有關(guān)，小迎角時(shí)升力(系數(shù))隨迎角直線增長(zhǎng)，到一定界限后迎角增大升力反而急速減小，這個(gè)分界叫臨界迎角。

The lift force mainly depends on four factors: a. The lift force is proportional to the wing area; b. The lift is proportional to the square of the aircraft speed. Under the same conditions, the faster the flight speed, the greater the lift; c. The lift is related to the airfoil. Generally, the lift of an asymmetric airfoil wing is large; d. The lift is related to the angle of attack. When the angle of attack is small, the lift (coefficient) increases linearly with the angle of attack. When the angle of attack reaches a certain limit, the lift decreases rapidly when the angle of attack increases. This boundary is called the critical angle of attack.

機(jī)翼和水平尾翼除產(chǎn)生升力外也產(chǎn)生阻力，其他部件一般只產(chǎn)生阻力。

Wing and horizontal tail generate drag in addition to lift, and other components generally only generate drag.

2、平飛

2. Level flight

水平勻速直線飛行叫平飛。平飛是基本的飛行姿態(tài)。維持平飛的條件是：升力等于重力，拉力等于阻力。由于升力、阻力都和飛行速度有關(guān)，一架原來(lái)平飛中的模型如果增大了馬力，拉力就會(huì)大于阻力使飛行速度加快。

Horizontal uniform straight flight is called level flight. Level flight is the basic flight attitude. The condition for maintaining level flight is that lift equals gravity and pull equals resistance. Since the lift and drag are related to the flight speed, if the horsepower of an original model in level flight is increased, the pull will be greater than the drag to speed up the flight.

飛行速度加快后，升力隨之增大，升力大于重力模型將逐漸爬升。為了使模型在較大馬力和飛行速度下仍保持平飛，就須相應(yīng)減小迎角。反之，為了使模型在較小馬力和速度條件下維持平飛，就須相應(yīng)的加大迎角。所以操縱(調(diào)整)模型到平飛狀態(tài)，實(shí)質(zhì)上是發(fā)動(dòng)機(jī)馬力和飛行迎角的正確匹配。

When the flight speed is increased, the lift will increase, and the model will climb gradually when the lift is greater than the gravity. In order to make the model maintain level flight under higher horsepower and flight speed, the angle of attack must be reduced accordingly. On the contrary, in order to maintain level flight of the model at low horsepower and speed, it is necessary to increase the angle of attack accordingly. Therefore, the control (adjustment) of the model to level flight is essentially the correct match of engine horsepower and flight angle of attack.

3、爬升

3. Climb

前面提到模型平飛時(shí)如加大馬力就轉(zhuǎn)為爬升的情況。爬升軌跡與水平面形成的夾角叫爬升角。一定馬力在一定爬升角條件下可能達(dá)到新的力平衡，模型進(jìn)入穩(wěn)定爬升狀態(tài)(速度和爬角都保持不變)。穩(wěn)定爬升的具體條件是：拉力等于阻力加重力向后的分力(F="X十Gsinθ);升力等于重力的另一分力(Y=GCosθ)。爬升時(shí)一部分重力由拉力負(fù)擔(dān)，所以需要較大的拉力，升力的負(fù)擔(dān)反而減少了。

As mentioned earlier, when the model is in level flight, if you increase the horsepower, it will turn to climb. The included angle formed by the climbing track and the horizontal plane is called the climbing angle. A certain horsepower may reach a new force balance under a certain climbing angle, and the model will enter a stable climbing state (speed and climbing angle remain unchanged). The specific conditions for stable climbing are: the tension is equal to the drag plus the backward component of gravity (F="X+Gsin θ); The lift is equal to another component of gravity (Y=GCos θ)。 When climbing, part of the gravity is borne by the tension, so a larger tension is required, and the lifting force is reduced.

和平飛相似，為了保持一定爬升角條件下的穩(wěn)定爬升，也需要馬力和迎角的恰當(dāng)匹配。打破了這種匹配將不能保持穩(wěn)定爬升。例如馬力增大將引起速度增大，升力增大，使爬升角增大。如馬力太大，將使爬升角不斷增大，模型沿弧形軌跡爬升，這就是常見(jiàn)的拉翻現(xiàn)象。

Similar to peaceful flight, in order to maintain a stable climb at a certain angle of climb, proper matching of horsepower and angle of attack is also required. If this match is broken, you will not be able to maintain a stable climb. For example, the increase of horsepower will lead to the increase of speed, lift and climbing angle. If the horsepower is too large, the climbing angle will increase continuously, and the model will climb along the arc track, which is a common phenomenon of rollover.

4、滑翔

4. Gliding

滑翔是沒(méi)有動(dòng)力的飛行?；钑r(shí)，模型的阻力由重力的分力平衡，所以滑翔只能沿斜線向下飛行?；柢壽E與水平面的夾角叫滑翔角。

Gliding is a flight without power. When gliding, the resistance of the model is balanced by the component of gravity, so gliding can only fly downward along an oblique line. The angle between the glide path and the horizontal plane is called glide angle.

穩(wěn)定滑翔(滑翔角、滑翔速度均保持不變)的條件是：阻力等于重力的向前分力(X=GSinθ);升力等于重力的另一分力(Y=GCosθ)。

The condition for stable gliding (both gliding angle and gliding speed remain unchanged) is that the resistance is equal to the forward component of gravity (X=GSin θ); The lift is equal to another component of gravity (Y=GCos θ)。

滑翔角是滑翔性能的重要方面?；杞窃叫?，在同一高度的滑翔距離越遠(yuǎn)?；杈嚯x(L)與下降高度(h)的比值叫滑翔比(k)，滑翔比等于滑翔角的余切滑翔比，等于模型升力與阻力之比(升阻比)。

Gliding angle is an important aspect of gliding performance. The smaller the gliding angle, the farther the gliding distance at the same altitude. The ratio of the glide distance (L) to the descent height (h) is called the glide ratio (k). The glide ratio is equal to the cotangent glide ratio of the glide angle and the ratio of the model lift to the drag (lift drag ratio).

滑翔速度是滑翔性能的另一個(gè)重要方面。模型升力系數(shù)越大，滑翔速度越小;模型翼載荷越大，滑翔速度越大。調(diào)整某一架模型飛機(jī)時(shí)，主要用升降調(diào)整片和前后移動(dòng)來(lái)改變機(jī)翼迎角以達(dá)到改變滑翔狀態(tài)的目的。更多相關(guān)事項(xiàng)就來(lái)我們網(wǎng)站http://m.zaiguo.cn咨詢(xún)了解吧！

Gliding speed is another important aspect of gliding performance. The larger the lift coefficient of the model is, the smaller the gliding speed is; The higher the model wing load, the higher the gliding speed. When adjusting a certain model aircraft, the main purpose is to change the angle of attack of the wing by moving the lift adjustment piece and the center of gravity forward and backward to change the gliding state. Come to our website for more information http://m.zaiguo.cn Ask and understand!