"ask"airfoil f-16
05-19-2008, 02:03 PM
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RE: "ask"airfoil f-16
Ok, found it!!
http://www.pdas.com/sections6a.htm#64A204
Got a nice table so you can plot the foil useing the percent of cord to heights above and below the referance line!
http://www.pdas.com/sections6a.htm#64A204
Got a nice table so you can plot the foil useing the percent of cord to heights above and below the referance line!
05-20-2008, 10:49 AM
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RE: "ask"airfoil f-16
That web site above dose not have thw McD D F-16 listed! I check it first as it is on of the eirst places I go for foil data. I could send you the outline in PDF form if that will Help!
05-20-2008, 01:58 PM
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RE: "ask"airfoil f-16
So you agree then, about the airfoil anyway. PLEASE do'nt shoot the messanger!
http://www.aerospaceweb.org/aircraft/fighter/f16/
http://www.aerospaceweb.org/aircraft/fighter/f16/
05-20-2008, 08:51 PM
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RE: "ask"airfoil f-16
Give me some specifics on the wing and I can generate the planform and templates for you if thats what you need?....
Need span, root and tip cord, LE sweep. N64204 airfoil below.
Need span, root and tip cord, LE sweep. N64204 airfoil below.
05-21-2008, 06:35 AM
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RE: "ask"airfoil f-16
TO lov2flyrc
I MADE MOLD F-16 FROM WOOD
AND I 'M NOT PROFESSIONAL
Length :1878 MM & WINGSPAN : 1300 MM
HALFSPAN : 450 MM
ROOT : 509 MM
TIP CHORD : 167 MM
SWEEP : I DONT KNOW
PLEASE IF ANY THING IS WRONG TELL ME
THANKS FOR EVERY ONE
I MADE MOLD F-16 FROM WOOD
AND I 'M NOT PROFESSIONAL
Length :1878 MM & WINGSPAN : 1300 MM
HALFSPAN : 450 MM
ROOT : 509 MM
TIP CHORD : 167 MM
SWEEP : I DONT KNOW
PLEASE IF ANY THING IS WRONG TELL ME
THANKS FOR EVERY ONE
05-21-2008, 11:54 AM
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RE: "ask"airfoil f-16
ORIGINAL: poxy
TO lov2flyrc
I MADE MOLD F-16 FROM WOOD
AND I 'M NOT PROFESSIONAL
Length :1878 MM & WINGSPAN : 1300 MM
HALFSPAN : 450 MM
ROOT : 509 MM
TIP CHORD : 167 MM
SWEEP : I DONT KNOW
PLEASE IF ANY THING IS WRONG TELL ME
THANKS FOR EVERY ONE
TO lov2flyrc
I MADE MOLD F-16 FROM WOOD
AND I 'M NOT PROFESSIONAL
Length :1878 MM & WINGSPAN : 1300 MM
HALFSPAN : 450 MM
ROOT : 509 MM
TIP CHORD : 167 MM
SWEEP : I DONT KNOW
PLEASE IF ANY THING IS WRONG TELL ME
THANKS FOR EVERY ONE
Need to know the sweep angle, this is the offset measurement from the root LE to the tip LE. Provide me this and I can mock up the wing. How do you plan to make them? Wood, foam, composite? Need to know how you want the templates supplied.
05-21-2008, 01:11 PM
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RE: "ask"airfoil f-16
Found the best 3-view image I could and brought it into AutoCAD and rubber sheeted it the specified Length and span and came up with the following!
Inboard foil: length = 11’-10 ½”
Outboard foil length = 3’ - 6”
Wing panel length = 10’-10 ½”
Looking at all the 3-view general the following thoughts:
The top of wing is flat, dihedral comes from the raise in the bottom of the wing.
LE is perpendicular the CL of A/C, which translated into a TE setback at tip of 8’- 4 ½” or 38°.
Looking at the image it looks like there is washout as the LE CL runs towards the bottom of the tip rib, I am thinking till the foil aft top is basically straight with the A/C CL, giving a sweep angle of 3°.
If I did the math right POXY's scale down is a multiplier of 0.137600806!
Inboard foil: length = 11’-10 ½”
Outboard foil length = 3’ - 6”
Wing panel length = 10’-10 ½”
Looking at all the 3-view general the following thoughts:
The top of wing is flat, dihedral comes from the raise in the bottom of the wing.
LE is perpendicular the CL of A/C, which translated into a TE setback at tip of 8’- 4 ½” or 38°.
Looking at the image it looks like there is washout as the LE CL runs towards the bottom of the tip rib, I am thinking till the foil aft top is basically straight with the A/C CL, giving a sweep angle of 3°.
If I did the math right POXY's scale down is a multiplier of 0.137600806!
05-21-2008, 04:13 PM
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RE: "ask"airfoil f-16
Your numbers seem to be scaled OK, and varied only slightly from mine. I believe this is due to the different images we use to generate them. Your scale is a little strange 1:7.268307692 (31' span x12 = 372", 372" x 25.4 = 9448.8 mm, 9448.8 / 1300 = 7.268307692 your scaled number for span)
05-22-2008, 02:21 AM
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RE: "ask"airfoil f-16
Excuse me for butting in guys, but whilst that may be the correct wing section for the root of the F-16, surely it is not correct for the tip. The f-16 tip appears to have a lot more camber as well as washout. Or am I seeing things?
Regards,
John
Regards,
John
05-22-2008, 09:34 AM
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RE: "ask"airfoil f-16
John
The 64A204 is listed in more then one set of offical specs. as both root and tip foils.
poxy
E-16 wing span is 31' x 12 = 372" of span, take this x 25.4 to get the 9448.8 mm real world wing span. Divid that by your scaled wing span of 1300 = 7.26807692. This gives you your scale factor of 1:7.2607692, or multiply the real world dimension by 0.137583608 to get a scaled length of your item in (mm).
The 64A204 is listed in more then one set of offical specs. as both root and tip foils.
poxy
E-16 wing span is 31' x 12 = 372" of span, take this x 25.4 to get the 9448.8 mm real world wing span. Divid that by your scaled wing span of 1300 = 7.26807692. This gives you your scale factor of 1:7.2607692, or multiply the real world dimension by 0.137583608 to get a scaled length of your item in (mm).