ajnl Posted March 15, 2012 Posted March 15, 2012 So i'm studying Aeronautical Engineering and we have a project where we have to design an airplane. Its more of conceptual design. Wasn't sure what area to post this in. Some more technical data Cruise speed: 700km/h Max speed: 750km/h Cruise altitude: 10,000m (about 30,000ft) Max take-off weight (MTOW): 5,000kg Payload: about 500kg Length: 13m Wing span: 14m Take-off speed: 200km/h Airfoil: NLF(1)-0015 C_lmax: about 1.2 C_Lmax: about 1.0 Its a conceptual design for a cargo plane. Like carrying important cargo (documents, mail, etc), diamonds, etc. Quote
rolf Posted March 15, 2012 Posted March 15, 2012 Dude, copy of a Cessna 510 But nice work. Anyway, how do you calculate those properties? And what are C_Imax and C_Lmax? Quote
ajnl Posted March 15, 2012 Author Posted March 15, 2012 (edited) Dude, copy of a Cessna 510 But nice work. Anyway, how do you calculate those properties? And what are C_Imax and C_Lmax? Hahaha, they all look similar. Actually we didn't look at that plane at all, BUT ours is very very similar to the Citation CJ2 We didn't calculate the C_lmax, it was given in the worldofkrauss.com database. C_l is the 2d coefficient of lift, the C_L is the 3d coefficient of lift. So: C_L = (C_l* f * A)/(A + 2) f = platform factor A = Aspect ratio We wanted a Cruise speed of 700 km/h, so our calculations went backwards, to have that velocity. Wing span comes from the W/S that you want. Weight/Surface area. Use the MTOW as weight, so you can find a S. From there b (wing span) can b found. Altitude comes from the fact we are using a turbo fan engine, optimum altitude is around 25,000 - 30,000 ish. This is only a conceptual design project, so we won't find it exactly. Most aircraft of this size will take off around 200 - 220km/h. Of course, that is also something you decide, so calculate backwards. We want it to take off from any major airport in Europe and Africa, so we wanted to keep the take-off speed low. Edited March 15, 2012 by ajnl Quote
Esteb@n24 Posted March 15, 2012 Posted March 15, 2012 C_l is the 2d coefficient of lift, the C_L is the 3d coefficient of lift. So: C_L = (C_l* f * A)/(A + 2) looks nice. btw u have pilot licence? Quote
ajnl Posted March 15, 2012 Author Posted March 15, 2012 looks nice. btw u have pilot licence? Thanks . Nope I don't, but i'm hoping to join the Dutch airforce once i'm done with my study. Quote
rolf Posted March 15, 2012 Posted March 15, 2012 Ah, indeed. I lost the correct one, I looked up for VLJ and saw the 510 as only hit, but it is indeed a closely related to the Citation series. Nice explanation, I've always been somewhat interested in things that fly (although I want a Huey ), and this gives me more information which I'll probably never use but is fun to know. Quote
ajnl Posted March 15, 2012 Author Posted March 15, 2012 hahaha, well if you want more information, I can give you a lot more lol Quote
WhiteCat Posted March 16, 2012 Posted March 16, 2012 Altho I dont understand aloth from this I know someone who follows this aswell in the netherlands in Delft. Only know it's not easy at all so props to you Quote
ajnl Posted March 17, 2012 Author Posted March 17, 2012 Altho I dont understand aloth from this I know someone who follows this aswell in the netherlands in Delft. Only know it's not easy at all so props to you Does he go to the TU or InHolland University of Applied Sciences? Quote
WhiteCat Posted March 17, 2012 Posted March 17, 2012 Does he go to the TU or InHolland University of Applied Sciences? TU Delft Quote
ajnl Posted March 19, 2012 Author Posted March 19, 2012 TU Delft Ah so he is in Aerospace Engineering. That is a bit harder still than what I do Quote
WhiteCat Posted March 19, 2012 Posted March 19, 2012 Ah so he is in Aerospace Engineering. That is a bit harder still than what I do Oh right yeah he does that & oh oke haha Quote
Recommended Posts
Join the conversation
You can post now and register later. If you have an account, sign in now to post with your account.