Can't read or understand your language, but really nice build. The modell seems to be a little bit tail heavy, so you need to add a little weight to the front. However, I asume others told you this already. Keep up the good work!
good work mite need bigger prop or motor need prop insert and check CG but all good have fun :)
@daviddavids28844 жыл бұрын
some info. at 12:07, prop INSERT Needed !!! at 12:42, not enough distance between the wing and the stabs. TOO much distance between the wing and the prop. the model is under-prop'd --- this is not necessarily a bad thing, on a slow-flyer. if you would like to improve your airframe designing skills, Learn to See PROPORTIONS. the use of correct proportions is KEY to good airframe design. note that elevator TRIM determines the cruising airspeed. when elevator is trimmed, for a given airspeed, a pilot does not have to fly the elevator, all of the time. (most models will cruise at 2/3 of maximum throttle, or less. Assuming most of the flaws are corrected, you will then need to determine the best nominal, throttle setting. (use left hand to) manipulate the tx trim Switches, in order to adjust trims WHILE the model flying. a pilot should learn about gliding. when gliding a powered model, a pilot must fly the elevator. because, the elevator trim that is correct for powered flight, is not correct for gliding. as discussed, the location of EXCESS mass, at the Tail, results in Tail-heaviness in the model's dom. dom is distribution of mass. it should be understood that if the cg is located aft of THIRTY percent of chord, the model is NOT Correctly balanced ! googletranslate upload.wikimedia.org/wikipedia/commons/thumb/a/ad/Cessna_150.svg/1044px-Cessna_150.svg.png this (accurate) illustration is Very informative. the vector of the thrust line can be understood. the parallel-ness to the thrust line, of the wing and h-stab can be seen. the advantages / efficiency of using a flat-bottomed profile can be seen. also, the ideal location of the c-m is indicated. c-m is center of mass. googetranslate e thrustnd the ideal location of the c-m is indicated. c-m is center of mass. s3.amazonaws.com/assets.flitetest.com/article_images/medium/truecg-jpg_1384168691.jpg
some info. good work. here are some things that could have been done, more-correctly. at 1:50, where a 'built-up' (half) main spar design is used, the 'layering' of material is less-effective, than the use of Right-angles. the main spar Should be located at thirty percent of chord. chord refers to the distance between the leading and trailing edges of a wing. (plan the (internal) main spar structure to be a rectangular, span-wise, tube. and avoid layering. at 2:47, this 'step' at the underside of the main wing trailing edge should Not be there --- this is a fact; not an opinion. at 2:50, this not an optimal profile. compare the (orig) clark-y profile. (such a profile can be, correctly, designed for any project; by using Ratios / percentages. the profile should be thickest at Thirty percent of chord; and maximum thickness is equal to 11.7 percent (of chord). the shape at leading edge is a Key part of the design. see at linked drawing, positive aoa is built into this profile/airfoil, such that, the wing can be mounted at (relative) zero-degrees aoa. aoa is angle of attack. at 3:03, the central main spar Should be located at thirty percent of chord. thirty percent is also the ideal location of cg. at 4:05, the aspect ratio (ar) of this wing is Too low. ar is a comparison of wingspan to wing chord. (imo, based on what is typical, chord should be reduced by about two inches; or more, depending on the flying weight; all-up-weight (auw). at 4:28, the rudder hinge SHOULD align with a point that is located at seventy percent of the vert-stab Root chord ! at 5:21, the use of spring-loading at a control surface hinge Makes No sense. at 6:18, 6:55, Over-complicated and HEAVY stab mounting scheme! equals Excess Mass, At the Tail !!! at 8:18, elevator control horn Should be located so that Clearance, at the rudder, is adequate ! removal of material at the lower edge of the rudder is Not recommended. (there are TWO solutions to the clearance issue. 1) locate the rudder trailing edge aligned with the elevator hinge line or 2) use what is called a SPLIT-elevator.) (same as the rudder) elevator chord should be equal to thirty percent of the horiz-stab root chord. the root chords of the stabs should be Equal. it may be appropriate to add a spar to the horiz-stab. use bamboo kabob skewer. at 9:27, sorry, this spring-loaded control linkage scheme is NOT a good one. the result is the presence of a load on each servo, ALL of the Time.! googletranslate clark-y profile en.wikipedia.org/wiki/Clark_Y_airfoil 1.bp.blogspot.com/-5C8vhlmhBOk/VRe3o3Jt3yI/AAAAAAAABrI/EEgVHXkLvbY/s1600/clark%2By.gif
@ここん東西-p9l4 жыл бұрын
Thank you for telling me a lot. I want to study more.