Author Topic: Draining E in turns  (Read 10601 times)

Offline Crumpp

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Draining E in turns
« Reply #90 on: August 28, 2004, 09:42:43 AM »
I just did a quick "flight test" in AH offline.

I upped an FW-190A5 with full fuel and a 500kg bomb.

Climbed to 3000 feet, trimmed for level flight at a speed of 250 mph IAS.

When I released the bomb, hand off the controls, the plane rose to a VSI of 250 FPM and I gained an average of 200 feet in altitude for a 1000 lb loss in weight.


When I took 25 percent fuel the effect was the same.

At 25 percent fuel under the same flight conditions I pulled a 70-80 degree bank.

The slowly went nose down to a VSI close to max and I lost some altitude.  However the A/C quickly self recovered leaving me level, at the same altitude and at a faster.

Not a very exact test but enough to know the effects of weight change are not very pronounced in the game.

Crumpp

Offline Crumpp

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Draining E in turns
« Reply #91 on: August 28, 2004, 09:44:11 AM »
Quote
not 4 times, but done gently enough it's possible.


I agree.  The contention is on extreme angle break turns which are so common in the game.

Crumpp

Offline hitech

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Draining E in turns
« Reply #92 on: August 28, 2004, 10:32:56 AM »
Crumpp: The effects of weight change in the game are exatly what they should be. Once again before you make claims like "not very pronounced"  produce numbers what they realy should be, Then compair them to the AH results.

Offline Crumpp

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Draining E in turns
« Reply #93 on: August 28, 2004, 12:03:31 PM »
Quote
Crumpp: The effects of weight change in the game are exatly what they should be. Once again before you make claims like "not very pronounced" produce numbers what they realy should be, Then compair them to the AH results.


Your absolute right.  "not very pronounced" is very vague.  I will withdraw that.

However the second part of the test.  The one most relevant to this thread is very valid.  A/C do not self recover from a spiral dive.  That is exactly why it is called a "Graveyard Spin".  It will continue to spiral with no appreciable out of trim forces to warn the pilot.  So instead fo having to expend E to counteract the forces and remain in a Level turn, the Plane automatically does it for you.  So you wind up with an E excess at the end of the turn.

http://www.av8n.com/how/htm/aoastab.html#fig-spiral-75

http://www.av8n.com/how/htm/roll.html#fig-footprint-vec

http://www.av8n.com/how/htm/aoastab.html#fig-pitch-damping

Quote
It is still trimmed for cruise angle of attack.



Quote
In a coordinated turn, the aircraft is happy to continue turning forever; it will definitely not have any tendency to return to wings-level flight. Indeed, it will have the opposite tendency, called the overbanking tendency, which we now discuss.


Lastly,  Do not think for an instant that I think AH is "all messed up".  It is in fact IMO and experience the best  MMOL flight sim available to today.  There are some with better eye-candy but when the rubber meets the road their eye candy cannot cover up their flight model.

We also know that you guys have not gotten around to tweaking the flight models yet.  So I imagine some of the "things that make you go MMMMMMM" will in all likelyhood disappear.

Crumpp

Offline Badboy

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Re: Draining E in turns
« Reply #94 on: August 28, 2004, 01:41:49 PM »
Hi Guys,

Just jumping in here in the hope I can help.

Quote
Originally posted by GODO
But what we see is that small planes like 190s or 109s lose E much faster than much larger ones like P51s or Spits when turning well above stall speeds.


How quickly an aircraft gains or loses energy in a turn depends on its specific excess power, and while that is influenced by the size of the aircraft, that's not the only thing to be considered. If you only look at the size of the aircraft, and leave out other important considerations, it is possible you will arrive at erroneous conclusions.    

Here is an EM diagram for the P-51D, the Fw190D9 and the Fw190A5 from Aces High (Haven't done them for Aces High 2 yet) and it shows that, for the conditions indicated in the diagram, both 190s will lose energy more rapidly than the P-51D.  



So, if you are seeing that behaviour in Aces High, it is consistent with this analysis of their flight models. Personally, this characteristic of the Fw190 series in AH makes them extremely dangerous, because they bleed energy more rapidly in a hard turn, if you engage one in a P-51D at high speed, you know they are going to be able to reduce their turn radius more quickly than you and get the first shot. In a one circle fight, or a scissors, that will be fatal. Almost every Fw190 driver I have come across in Aces High is able to take advantage of that to good effect. The ability of the P-51D to sustain its energy in the turn is only an advantage if the P-51D can survive long enough to use it. There are ways to do that, but that becomes a discussion about air combat, and not aircraft performance.  

Quote

I understand than large winged planes with smaller wingloading will keep turning tighter and at slower speed than small planes with more wingload, but the small ones should lose speed at a lower rate and the others until they reach stall speeds.

Where am I wrong?


As others in this thread have said, you can’t simply focus on the size of an aircraft, and ignore everything else, and expect to reach valid conclusions, you really do need to consider everything.

The EM diagram I posted above does include everything, and it shows that the behaviour you are seeing should be expected, for those aircraft, under those conditions. That of course begs the question, how close are those diagrams to the performance of their real world counterparts? I can only answer that by saying that I have tested a number of flight simulations, the other online simulations, and some big name boxed games, and produced overlays for their aircraft versus some real WW2 fighters for an article I’m writing for SimHQ. The good news is that the AH aircraft show a breathtakingly good correspondence, and are generally closer than the other simulations, in some cases Aces High’s superiority in that respect is extreme!

I Hope that is helpful.


Badboy

PS, Kudos to HTC on AH2... Good work guys!
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Offline Crumpp

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Draining E in turns
« Reply #95 on: August 28, 2004, 02:07:10 PM »
Repost Hitech so you can see the math:


------------------------------------------------------------------------------------

Ok,

Did some calculations:

First I did up the Cl that was used in the Drag formula.

The weight data for the FW-190 came from Pilots Manual. The weight data for the Spitfire came from:

http://www.fourthfightergroup.com/eagles/jl165.html

The P51D was much harder. I ran into the same problem with the Focke-Wulf. Empty Weight and Max Weight were easy to find but the takeoff weight of a regular fighter not burdened with extra's was slightly harder. On site listed 10,000 lbs and another site listed 9800 lbs. I chose the lesser weight as I felt it was the best data available.

All A/C where calculated under the following conditions:

Temperature - 65 *F
Atmospheric Pressure - 14.696 PSI

Speed = 300 mph

Using the following formula:

http://www.grc.nasa.gov/WWW/K-12/airplane/liftco.html

FW190A8 - Weight = 4272kgs
Wing Area = 196.98 sq. feet
Cl = .651727567

Spitfire Mk IX Merlin 66 (+25)- Weight = 7400kgs
Wing Area = 242 sq feet
Cl = .416810811

P51D- Weight = 9800lbs
Wing Area = 882.2
Cl = .568493091

For the drag calculations I used "Cd wet" out of David Lednicer's article, as they are all real world tested with his sources listed at the bottom.

http://www.thetongsweb.net/AH/EAAjanuary1999.pdf

For reference Area I used the Wet Area and the used the following formula:

http://www.grc.nasa.gov/WWW/K-12/airplane/drageq.html

FW-190 Drag = 382.85
CDw = .0071
Ref Area = 735 sq ft

Spitfire Drag = 396.27
CDw = .0065
Ref Area = 831.2 sq ft

P51D Drag = 343.56
CDw = .0053
Ref Area = 882.2 sq ft



quote:
--------------------------------------------------------------------------------
I received this document from the Vought archives and scanned it. It shows the P-51B Cdo at .017.
--------------------------------------------------------------------------------



David Lednicer mentions some Snafu's over the P51's drag testing. Seems there a bunch of calculated Cd's and even a tested Cd or two running around that are wrong. Apparently they tested it without adding things like the exhaust stacks to the test A/C in the tunnel. Nevertheless it does have an extremely low Cd.

P51 was an excellent fighter.

Generally speaking, lower wing loaded planes have more surface and therefore more parasitic drag. Unless of course there is a large size difference in the first place between the planes.

Since pulling a tight bank will cause and increase in speed or force the pilot use excess speed to pay for the altitude you maintain the plane with the highest parasitic drag will bleed the most energy due to drag.

Yes Low-wing loaded planes can turn the same angle as a high wing loaded plane and pay less for it. However when turning at their max turn rate it they pay the price like every other wing.

http://www.av8n.com/how/htm/aoastab...ig-spiral-start


quote:
--------------------------------------------------------------------------------
In order to produce 4 tons of lift, the airplane must fly at roughly 200 knots --- twice the wings-level trim speed.
--------------------------------------------------------------------------------



Crumpp

Offline Crumpp

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Draining E in turns
« Reply #96 on: August 28, 2004, 02:27:41 PM »
Quote
Because the Spitfire's wing loading is much lower, it's Aspect ratio is higher then either aircraft mentioned, and the E Factor of the elliptical wing is REALLY good.


It's aspect ratio is NOT higher than either A/C mentioned.


The FW-190's Aspect Ratio is 6.01 in the FW-190A8.


In the FW-190A6 the wing was changed to accomidate the MG151's in the outboard postions AND to help offset the weight increase from the added armament and the extended engine mounts modified in the FW-190A5.

Aspect ratio FW-190A5 and below = 5.8

Aspect ratio FW-190A6 and above = 6.01

CG adjustments also occurred in the FW-190A8.

Crumpp

Offline gripen

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Draining E in turns
« Reply #97 on: August 28, 2004, 04:35:37 PM »
Quote
Originally posted by Crumpp

All A/C where calculated under the following conditions:

Temperature - 65 *F
Atmospheric Pressure - 14.696 PSI

Speed = 300 mph

Using the following formula:

http://www.grc.nasa.gov/WWW/K-12/airplane/liftco.html

FW190A8 - Weight = 4272kgs
Wing Area = 196.98 sq. feet
Cl = .651727567

Spitfire Mk IX Merlin 66 (+25)- Weight = 7400kgs
Wing Area = 242 sq feet
Cl = .416810811

P51D- Weight = 9800lbs
Wing Area = 882.2
Cl = .568493091


All the Cl values are wrong as well as the wing area of the P-51D. As an example Cl for the Fw 190 is calculated correctly above.

Quote
Originally posted by Crumpp

FW-190 Drag = 382.85
CDw = .0071
Ref Area = 735 sq ft

Spitfire Drag = 396.27
CDw = .0065
Ref Area = 831.2 sq ft

P51D Drag = 343.56
CDw = .0053
Ref Area = 882.2 sq ft


All drag values seem to be wrong? At least the unit is not newton nor kilopond nor pound.

Quote
Originally posted by Crumpp

It's aspect ratio is NOT higher than either A/C mentioned.


If the Spitfire had e factor say 0,8 and the Fw 190 say 0,7. Then the Spitfire had effective aspect ratio 4,49 and the Fw 190 4,21. Lednicer notes in the case of the Spitfire that "loading distribution is not elliptical, though it is probably the most optimum of the three from the induced drag standpoint".

Regarding Lednicer's flat plate values, it seems that these are for total drag ie include induced drag which mean that his values are actually quite close my quick and dirty values depending if flat plate area is calculated for Cd 1 or 1,28 (square).

Quote
Originally posted by Crumpp

Aspect ratio FW-190A5 and below = 5.8

Aspect ratio FW-190A6 and above = 6.01


Well, from the Fw 190A-1 onwards all the A-series Fw 190s had same wing area and span so these all had same aspect ratio 6,02 (18,3 m2 and 10,5 m). Some early A-0s had smaller wing which had aspect ratio 6,07 (14,9 m2 and 9,51 m).

gripen

Offline Angus

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Draining E in turns
« Reply #98 on: August 28, 2004, 05:16:50 PM »
Crumpp: this made me think:
"Since pulling a tight bank will cause and increase in speed or force the pilot use excess speed to pay for the altitude you maintain the plane with the highest parasitic drag will bleed the most energy due to drag.

Yes Low-wing loaded planes can turn the same angle as a high wing loaded plane and pay less for it. However when turning at their max turn rate it they pay the price like every other wing. "

No matter what your calculations show, bear in mind that the finest turning planes of WW2 had a low wingloading. Example: A6m.
Now, a fast aircraft with a low wingloading such as the Spitfire, also has a very good turning ability.

Heavy wingloading, no matter how you calculate, will always bleed everything, except sheer accumulated Newtons. A heavy plane will crash deeper into the ground, it may zoom better, apart from that it's all against the wind. No matter what you calculate.

I'll mail you an excel thingie to look at Newtons in a Climb.
I am no Excel expert, however Newtons are a calculable thing, and this particular formula did show something to me in a rather clear manner which was not to be haired out on these boards.

Regards..


Angus
It was very interesting to carry out the flight trials at Rechlin with the Spitfire and the Hurricane. Both types are very simple to fly compared to our aircraft, and childishly easy to take-off and land. (Werner Mölders)

Offline Crumpp

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Draining E in turns
« Reply #99 on: August 28, 2004, 06:03:38 PM »
My calcs aren't wrong Gripen.

The wing area I used for the P51D is: 234.976 sq ft.  

That is a misprint.  The Cl's are correct, however and feel free to calculate them yourself.

And post them in English units NOT metric, as mine are in, which you think are wrong.

I wrote David Lednicer to see if he has insight into this.  We are just flat out missing to many of the details.  

For example Gripen:

You list the wingtip E factor as .8 and the mustang as .75.  Where did you get this data?  You list the Spitfires as .95 while the NASA site clearly says the Spitfire had an E factor of 1.

The information that is out there is conflicting even among "official" sources.  Just look at the Mustang.  Since David actually build airplanes and analyzes past aircraft as a hobby he is probably in a better position to give us "the best" data available or at least the closest to actual performance.

Yet this Aircraft has E factor of .95.  Niether the FW 190's wing tips or the P51's were "square".  

 http://www.anycities.com/user/j22/j22/index.htm

And quit carrying your feelings in a glass jar.  Last thread as soon as you were questioned you became extremely rude.  Your starting it again.  

This is what I am trying to do:

1.  If you examine the loss records (which the Luftwaffe kept meticulous records of their casualties) you will find this pattern.

The pre-1943 trained pilots took losses on a pretty much steady curve from the beginning to the end of the war. It does go up some in the last years of war when pressure from the Allies in the West was at it's greatest (Big Week and Bodenplatte).  Their loss rate stays fairly constant and does not rise dramatically.

The post-1943 trained pilots died like flies with an almost 98 percent loss rate.  IF they survived to complete their sixth mission their chances of surviving until the end of war went up astronomically.  

After WWII there was a tendency to explain the Luftwaffe high victory levels on Aircraft performance.  

Later this was found not be true.  Because of the mound of data compiled to disprove the "wonder planes" theories the perception has been created that Luftwaffe planes were poor performers.

This can be seen in Authors such as Alfred Price and Peter Cayhill.  Much of the commentary by Price is in direct odds with Eric Browns.  Peter Cayhill, a noted spitfire historian, in his book "Combat Legends" takes a tactically sound interception and creates the perception the FW-190 was only good for a high-speed bounce.  That is in direct odds with the Luftwaffe pilot anecdotal evidence that says they routinely got into dogfights with the FW-190 AND gave as good as they got.

In fact the Luftwaffe took it's losses for the same reason it achieved it's victories.  Luftwaffe pilots had a much greater chance than an allied pilot to encounter the enemy.

Combine that with the tactical realities of the "Defense of the Reich" and it is easy to see why.  Men in combat don't say good things about their equipment if it sucks.  You won't hear statements like:

" Against 20 Russians trying to shoot you down or even 20 Spitfires, it can be exciting, even fun.  But Curve in towards 40 Fortresses and all your past sins flash before your eyes."

Oblt. Hans "Fips" Phillip, Kommandure JG1
FW-190A5 pilot

He was killed by P47's 4 days after that statement, seconds after downing his first B17.  The P47's were on his six as he attacked the B17.

One young Luftwaffe pilot who arrived in JG 26 in the summer of 1944 got to fly three combat missions in World War II.  Each mission had months in between the sorties because he was shot down each time he took off.  He was lucky and survived the war.  The day he graduated "flight school" he was the sole survivor, besides his instructor, of his student schwarm.  The instructor took them flying down a valley.  3 of the students crashed into the mountain at the end of it following the instructor.

2.  In my studies I have never found a situation yet where the science did not line up with history in the Air War.

3.  Since I am writing a book I am on an agenda.  Not the one you think though to "artificially inflate" my favorite planes performance.  There is a wealth of new information out there on these planes performances that has been declassified.  With the Internet access to such places as the Luft-archive and the National Archives it is even more widely available.  

I believe the actual plane performances will line up with the statistics.   This is a great forum to both get a good idea of the science behind the Aircraft and to gauge that performance.  In short it is a good tool.
 
Crumpp

Offline Crumpp

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Draining E in turns
« Reply #100 on: August 28, 2004, 06:06:44 PM »
Quote
I'll mail you an excel thingie to look at Newtons in a Climb.


Cool Angus!

Thanks bro.

Offline dtango

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Draining E in turns
« Reply #101 on: August 28, 2004, 09:16:42 PM »
Crummp:

Quote
Repost Hitech so you can see the math:

The math is for 1g level flight.  This is irrelevant if you're trying to compare total aircraft drag in a turn.  We've been asking you to calculate total drag in a turn.

Here's the deal - the simplified tota drag coeff eqn. is the following:

CD = CD0 + CDi

You've only attempted to calculate the above at 1g.  CDi increases in a turn and becomes even more dramatic the greater the Cl.  

Even using your calcs FW-190 (highest wingloaded a/c for comparison) has the greatest Cl hence the greatest Di even at 1g- just that at 1g Di contribution to total drag is only a small fraction of total drag.  

Now start increasing load factor for a turn and Di's contribution grows in an exponential progression with increasing load factor.

Here's the kicker which you are missing.  The FW-190 already has greater induced drag than the lower wing-loaded aircraft at 1g.  This doesn't change at 2g's, 3g's, or 4g's etc.  Infact Di's contribution to the % of total drag increases dramatically so that the higher induced drag of the 190 becomes more pronounced vs. the lower wing-loaded aircraft.

I'm tempted to post a table of calcs for you but I don't want to because my sense is that the only way you'll believe it is if you do the calcs yourself and visualize what is happening.  

Quote
My calcs aren't wrong Gripen....And post them in English units NOT metric, as mine are in, which you think are wrong.

Like gripen said your total drag values don't seem to be in line with anything.  If they are in lbs as you say then those values are way low.

Another alternative to try and understand why a better turning plane may lose E slower than a higher wingloaded plane is to study Badboy's EM chart he has posted and what he has stated.

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Offline Crumpp

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Draining E in turns
« Reply #102 on: August 28, 2004, 11:58:31 PM »
Quote
The math is for 1g level flight. This is irrelevant if you're trying to compare total aircraft drag in a turn. We've been asking you to calculate total drag in a turn.



I did and your right a higher wingloaded A/C does loose more energy in a turn.  The Cdi increases dramatically.  However I don't think it works like you are claiming.

First we know speed must increase or the A/C will have to trade it's speed to maintain altitude.

At speed:

Quote
At high airspeeds, parasite drag is dominant and induced drag becomes almost negligible.


http://www.av8n.com/how/htm/4forces.html#sec-induced-vs-parasite


You seem to be saying the Cl increases throughout the turn.  

Now we know the force of lift does not change:

http://www.av8n.com/how/htm/4forces.html#fig-force-ias


And the Cl goes down with speed:

http://www.av8n.com/how/htm/4forces.html#fig-coeff-ias

The Load factor is increased when G's are pulled:

http://www.av8n.com/how/htm/aoastab.html#fig-secant

And consequently:

Quote
When you enter a spiral dive, the wing area of the airplane doesn’t change, the density of the air (ñ) doesn’t change, and the coefficient of lift doesn’t change much, either.


http://www.av8n.com/how/htm/aoastab.html#eq-lift-again


So for the intial bank and angle of attack change you will get a penalty in a higher wingloaded plane from increased induced drag.  The rest of the high speed, high load turn the plane with the highest parasitic drag will be taking the biggest hit.

I came across a great diagram on the site but I can't find it now.  I will look for it in the morning.  Basically it showed that once the bank was made and speed increased, the relative wind was changed to the vector the aicraft was traveling in a co-ordinated turn.  In other words it was just like forward flight.

Crumpp

Offline gripen

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Draining E in turns
« Reply #103 on: August 29, 2004, 12:01:55 AM »
Quote
Originally posted by Crumpp
My calcs aren't wrong Gripen.

The wing area I used for the P51D is: 234.976 sq ft.  

That is a misprint.  The Cl's are correct, however and feel free to calculate them yourself.

And post them in English units NOT metric, as mine are in, which you think are wrong.


The lift coefficient is a dimensioless value. If calculation is correct Cl will be same regardless used unit system. And your Cl values are not true for 1 g and your drag values are  not true  for Lednicer's flat plate areas at 300 mph near sea level (real values are somewhere around 5000 N).

Quote
Originally posted by Crumpp
You list the wingtip E factor as .8 and the mustang as .75.  Where did you get this data?  You list the Spitfires as .95 while the NASA site clearly says the Spitfire had an E factor of 1.


Just study the Figure 2 in the Lednicers paper. The lift distribution of the Spitfire is not fully elliptical while best of the three. My numbers are purely approximated but probably quite close to the real.

Quote
Originally posted by Crumpp
Yet this Aircraft has E factor of .95.  Niether the FW 190's wing tips or the P51's were "square".  

 http://www.anycities.com/user/j22/j22/index.htm


Well, I don't put much weight to that site; the author uses same Cd0 for all Spitfire models despite radiator changes and Cd0 seems to be value which actually is total Cd in the Lednicer's paper.

Quote
Originally posted by Crumpp
And quit carrying your feelings in a glass jar.  Last thread as soon as you were questioned you became extremely rude.  Your starting it again.


Well, in last thread someone called me butthead, lawyer etc. And somehow you concluded that my statement that Clo of the wing profile must be tested in the wind tunnel means that 3D to 2D conversion is impossible according to me. And you also came up with numbers which you could not explain despite requested.

gripen

Offline dtango

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Draining E in turns
« Reply #104 on: August 29, 2004, 09:11:34 AM »
Quote
I did and your right a higher wingloaded A/C does loose more energy in a turn. The Cdi increases dramatically.

Great,  now we're getting somewhere! :)

Quote
However I don't think it works like you are claiming.

Let's work on this now...

I'm not sure where you thought I was saying Cl increases in a turn.  It would only increase if the pilot increased the AOA to pull a tighter turn.

Quote
And the Cl goes down with speed:

Remember we covered this before and you said you got it?  Cl does not vary with speed.  It varies with AOA.

If you decide to dive and gain airspeed yet maintain the same turn performance your Cl is not going to decrease at all because you'd be at the minimun holding the AOA for the turn you want.  If you relaxed your turn then sure your Cl would go down but Cl varies with AOA not airspeed.  Whatever the case calculating drag in a dive still uses the CD = CD0 + CDi relationship for starters.

2ndly when you're in a dive the vectors change as well.  The relationship that T opposes D directly and L opposes W directly no longer hold as they do for level flight.

In a dive the force equation we're interested in is:
F = T + Wsin(dive angle y) - D

Now you have a portion of weight that is counteracting drag as well.  Infact it becomes very significant and more pronounced the steeper the dive angle.  

For instance for an 8000 lbs aircraft, just at 10 degrees dive your adding an extra 1389 lbs of thurst force offset against total drag.

Tango, XO
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Tango / Tango412 412th FS Braunco Mustangs
"At times it seems like people think they can chuck bunch of anecdotes into some converter which comes up with the flight model." (Wmaker)