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Yep and the drag is increased to some degreeYes Glider its aerodynamics, and aerodynamics don't support your claim that induced drag is greatly increased with 17.3 degrees of sweep. Get my drift ?
Its the 'e' value thats missing for me. DO you know anywhere where these can be obtained? Its not just for this its something that I have looked for.You may doubt it all you want but I do have that information Glider:
Cdi = (Cl^2) / (pi * AR * e)
Try plotting in some figures and see what effect just a 10% increase in AR actually has on induced drag.
Nope, not when your used to figures of 16-25Is 7.23 not high ? And thats without considering wing sweep.
I wouldn't disagree with thisIts very close to the same Glider.
Stitch,
The Germans were fully capable of making laminar flow airfoils, however being well aware of its negative effects on lift and stalling characteristics it was decided not to use it on any a/c.
I thought the one that crashed actually crashed up in England at RAF Burtonwood and killed Major Frederic Borsodi.
I think the numbers speak for themselves. On top of these figures, the Me262 rolled poorly, the P-80 rolled extremely well. The P-80 also out-turned the Me262. I really cannot see any aspect of the Me262 that beats the P-80.
The P-80 would have blasted the Me262 from the skies with ease!
New research has revealed that the actual kill ratio was more like 6 to 1 and maybe 2 to 1 aganst Soviet Units. In either case the F-86 still had the upper hand on the MiG-15.The F86 wasn't as fast as the MiG-15, it wasn't as heavily armed and couldn't climb anywhere near as rapidly; three key attributes in air combat. Despite this, the kill ratio of F86:MiG-15 was about 1:13 if you included MiG pilots of all nationalities involved (Chinese, Korean and Russian).
In real life it goes like this. The P-80, is likely to be faster,more agile in a dogfight but the 262 have far superior firepower and better pilots. In realistic air warfare the aircrafts scores an equal due to better luthwaffe pilots and better guns
Hehe, testing at Wright Field showed the Me-262 to be faster, climb faster accelerate faster than the P-80A. So who'ever wrote that on the other forum didn't have a clue what he was talking about..
Judging by thatThe speed numbers seem to be representative for a single test. Judging from the mass test of 125 production Me-262A1 carried out in late 1944 the corresponding average speed at the given altitudes appears to be:
Sea level: 521 mp/h ( P-80´s best altitude, Me-262A beeing significantly slower here)
15.000 ft.: 537 mp/h (slightly slower than the P-80 here)
20.000ft.: 543 mp/h (best altitude for the Me-262, slightly faster here than the P-80)
33.000 ft.: 518 mp/h (slightly faster than the P-80, here)
40.000 ft. altitude is barely in within service ceiling of the Me-262A at a gross weight of in between 6000 Kg (=service ceiling 39.222 ft.) and 5000 Kg(= service ceiling 42.700 ft.). Depending on the load and state of the airplane it would do in between 440 and 465 mp/h at 40.000 ft.