Author Topic: Draining E in turns  (Read 12192 times)

Offline Crumpp

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« Reply #180 on: September 06, 2004, 12:18:47 PM »
I recalculated the figures for Nashwan and reposting it so he does not have to hunt for it.  Here are the results.

The FW-190 is at 1.42ata @ 2700U/min as my horsepower data is much more accurate for 4500 feet. All data is calculated at 356mph the max level speed of the FW-190A8 at that altitude and power setting. This forms the base information at which the performance at lower speeds can be assessed.

FW-190A8 (data is the same)
Wing area S (sq. feet) - 196.98
Airplane weight, lbs (as tested) - 9418
Wing span, ft - 34.45

Step B - performance #s at a known altitude


Altitude (feet) - 4500
Maximum speed (at test alt.- mph) - 356
Engine Horsepower (bhp at test alt) - 1730
Stall speed (mph, at test alt) - 110

speed (mph TAS) @ 4500 feet ASL
300

CL
0.229178

D(p)
952.5006

D(i)
132.1558

CL^2
0.052523

CD(tot)
0.026394

Drag (tot)
1084.6564

thrust (lb)
1667.946

excess power (bhp)
583.2895

P.E.
0.78153

Spitfire Mk IX Merlin 66 (+25) - This data represents full throttle height for the Spitfire and an easy point to calculate from. Since my data is much more complete for the FW-190 it is easier to identify the Spitfire's knowns and then establish the FW-190's performance at the same altitude. Initial data was calculated under the following known conditions:

Step A - Enter Aircraft dimension Data
Wing area S (sq. feet) - 242
Airplane weight, lbs (as tested) - 7400
Wing span, ft - 36.1

Step B - performance #s at a known altitude

Altitude (feet) - 4500
Maximum speed (at test alt.- mph) - 365
Engine Horsepower (bhp at test alt) - 2050
Stall speed (mph, at test alt) - 90


speed (mph TAS) @ 4500 feet ASL
300

CL
0.146573

D(p)
1089.133

D(i)
72.55357

CL^2
0.021484

CD(tot)
0.02301

Drag (tot)
1161.6864

thrust (lb)
1976.468

excess power (bhp)
814.7812

P.E.
0.78153

Data all came from the same sources.

Quote
That's unrammed, rammed would be somewhat lower HP.


Yeah I did not feel comfortable using it and did not bother to post the results.  In my experience the FW-190 and the Merlin Spitfire IX's maintained extremely similar horsepower outputs.  Do you think 1400 hp is a fair figure for the Merlin 61 at that altitude?  That is the same as the BMW-801D2 at 1.42ata @ 2700U/min at the comparision altitude.


Crumpp

Offline mw

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« Reply #181 on: September 06, 2004, 12:19:38 PM »
Quote

it seems to me JL 165 had the standard VIII/IX tropical filter without blanking plates.

That's what JF 934 had, and the speeds RR got for JL 165 are pretty close to JF 934.

Which is probably why they started fitting blanking plates to the Spit air intake.

Spitfire the History gives figures for 3 Spit VIIIs tested with the tropical filter, first the normal Spit VIII type, then with blanking plates fitted.

JF 275 went from 397 mph to 402 mph, JL 163 from 367 to 372 (MS gear), JF 707 363 to 370 (MS gear), EN 654 (PR XI) 381 to 391.5 (MS gear) 410 to 421 (FS gear)


Hmm, I think you may be on to something.    JL.165 did have the blanking plate installed at AAEE though.  Of course those results are rather porked anyway.

Offline MiloMorai

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« Reply #182 on: September 06, 2004, 12:30:10 PM »
That would be an improvement compared to your current state indeed. Why not go further, and stopping your old habit of jumping on your bandwagon and write hysterical posts every time the word '109' is cast? All threads with the slightest mentioning of axis stuff is loud of your manure and it`s really gets boring.

Offline Crumpp

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« Reply #183 on: September 06, 2004, 12:34:44 PM »
Quote
You've hit your own nuts there Izzy. As it is, you yourself love to compare rather high performing 109's to the lower performing Spitties. Last thing I saw is your chart a tad above in this thread.


 IMO the only meaningful comparison is a fighter's contemporary opponent.  Comparing "the best" with "worst" is completely counterproductive to developing an honest appraisal.  It leads to wrong conclusions.

Quote
Hmm, I think you may be on to something. JL.165 did have the blanking plate installed at AAEE though. Of course those results are rather porked anyway.


Anybody have any test data?

Crumpp

Offline VO101_Isegrim

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« Reply #184 on: September 06, 2004, 12:52:59 PM »
Quote
Originally posted by Nashwan

It's note a Vokes filter.

Seeing the new stuff MW has got of the RR tests of JL 165, it seems to me JL 165 had the standard VIII/IX tropical filter without blanking plates.


Nashwan, how come that you suddenly forget your own mother language in such times? Have you forgotten how to read?

JL 165`s report notes :

"New tropical pattern air intake without gauze, but blanking plate installed.  
No ice guard fitted in air intake.  "


Quote


That's what JF 934 had, and the speeds  RR got for JL 165 are pretty close to JF 934.
[/B]

Has as much to do with reality as the previous statement. You never out of manipulation and excuses, are you?



Quote

By the time A&AEE tested it, JL 165 was 12 mph slower at sea level, and had lost hundreds of ft/min in climb rate.


Typical Naswhan crap vs. facts type engagement.

Facts :
In october, with R-R`s tests, on +25lbs 362mph was measured on JL 165 at 2000ft.
A few months later, with A&AEEreached 360 mph at 2000ft with JL 165 on +25lbs.

Just read the two reports.



Quote

I'm still waiting for you to put JF 934 on your climb graph with the 109. You did after all claim you were just waiting for "serial production data", and JF 934 was a production aircraft shipped out to Australia for service.


So we are supposed to believe JF 934 with low altitude Merlin 66 could outlcimb the 300 lbs lighter Mk IX with high altitude Merlin 70?

Possible in times of desperate need,  Nashwan/MW fanboyworld, though...



Quote

This is coming from Isegrim, who has spent several years arguing that the estimated figures for JL 165 are the most accurate Spitfire Merlin 66 figures available. BS 543 and BS 551 should be ignored, because JL 165 was the only accurate data available. Now he's saying JL 165 data at 18 lbs isn't accurate at all.


Bark as desperately you want Nash1. Bull**** 543 and Bull**** 551 were experimental planes, rigged in a fashion no serial Spits were. Everyone ackknowladges this, expect you and that other partisan fanboy. Only the mentally challanged would choose to use experimental plane data, when serial plane results are available.

Luckily now new and accurate data, actually tested is available for the JL 165 at +18. It matches well other testing at +18lbs, and can be viewed as representative for serially produced Spits. Naturally, I will revise my older data and use the new, and better/higher data for the Spitfire. Unlike you, I am interested in the historical facts, not sorry fantasies.


Quote

Does this mean you are going to remove it from your climb graph, Isegrim?


Hmm, I would, provided the new and better JL 165 data was for Open radiators, which unfurtanately isn`t, and closed rads are hardly conform testing with the RAF, or any other airforce. Provide data for open rads, and you got my word it will be replaced with that one.

BTW, is that climb graph so irritating? Well if THAT`s irritating, ie. the ultimate version of the 109 giving a slap in the face of your Spits, how does you feel to see even the 109G doing 4800 fpm on a limited 1.3ata boost, a full year before those Spit LFs appeared in meaningless numbers?



Quote

Which is probably why they started fitting blanking plates to the Spit air intake.


I`ll let you argue then with Mike wheter this was a problem on Spits or not in ETO. You should really decide now, over those many versions you made up till now... ;)


Quote
[/b]
Spitfire the History gives figures for 3 Spit VIIIs tested with the tropical filter, first the normal Spit VIII type, then with blanking plates fitted.

JF 275 went from 397 mph to 402 mph, JL 163 from 367 to 372 (MS gear), JF 707 363 to 370 (MS gear), EN 654 (PR XI) 381 to 391.5 (MS gear) 410 to 421 (FS gear) [/B]


That`s a staggering 5 mph increase. Better question is, how much of that was implemented in operational service.

Offline Angus

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« Reply #185 on: September 06, 2004, 01:23:46 PM »
"So we are supposed to believe JF 934 with low altitude Merlin 66 could outlcimb the 300 lbs lighter Mk IX with high altitude Merlin 70? "

At low alt I would actually expect that it could, with the climbing rate crossing in the 70's favour at higher altitude.
Not sure how much of a difference 300 lbs are, could of course calibrate it into Newtons and look for the true percentage in energy value.

Umm, does anyone have power curves or data for the 66 and 70?
Secondary stage alt?
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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« Reply #186 on: September 06, 2004, 01:57:36 PM »
FW-190A5 Power setting is at 1.42ata @ 2700U/min.

Step A - Enter Aircraft dimension Data
Wing area S (sq. feet) - 196.98
Airplane weight, lbs (as tested) - 9052.18
Wing span, ft - 34.45
   
Step B - performance #s at a known altitude
    
    
Altitude (feet) - 13000
Maximum speed (at test alt.- mph) - 383
Engine Horsepower (bhp at test alt) - 1400
Stall speed (mph, at test alt) - 110

speed (mph TAS)
300

CL
0.287507
D(p)
598.8078

D(i)
159.3517

CL^2
0.08266

CD(tot)
0.02408

Drag (tot)
758.15952

thrust (lb)
1314.365

excess power (bhp)
556.2053

P.E.
0.761023


Spitfire Mk IX Merlin 61 (+12)
Level speed data is from:
http://www.fourthfightergroup.com/eagles/bf274.html

Table IV Level Speeds.  You can see the Spirfire is at (+15.2) boost and I tend to think if 1565hp is full throttle height output @ 15400 for a Merlin 61 @ (+15) emergency power then it's output is probably higher than 1400hp.  

The FW-190 only gains about 30 hp between 13,000 feet and full throttle height at 22,000 feet ASL.

Unrammed the FW-190 only achieves around 1490hp at 22,000 feet ASL.  


Step A - Enter Aircraft dimension Data
Wing area S (sq. feet) - 242
Airplane weight, lbs (as tested) - 7480
Wing span, ft - 36.1
   
Step B - performance #s at a known altitude
    
    
Altitude (feet) - 13,000
Maximum speed (at test alt.- mph) - 370
Engine Horsepower (bhp at test alt) - 1400
Stall speed (mph, at test alt) - 90


speed (mph TAS)
300

CL
0.193377

D(p)
685.8562

D(i)
96.7565

CL^2
0.037395

CD(tot)
0.020232

Drag (tot)
782.61269

thrust (lb)
1314.365

excess power (bhp)
531.7521

P.E.
0.761023

Crumpp

Offline gripen

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« Reply #187 on: September 06, 2004, 03:57:03 PM »
I wondered a bit why could not reach same numbers with Zigrat's spreadsheet as with my own. After some crosschecking I found out that there appear to be a conversion error in the Zigrat's sheet; AFAIK one mile is 5280 ft and Zigrat's uses 5350 for mph to ft/s conversion. In addition I changed density formula (for standard atmosphere) to a bit more accurate:

rho=rho_0*(1.- 6.8755856*10^-6 * h)^4.2558797 h<36,089.24ft

where rho_0 = 0.002376892 slugs/ft^3

With these modifications Zigrat's spreadsheet gives same values with good enough accuracy (several decimals).

The e factor in the Zigrat's sheet seems to be modeled with somekind of formula which is based on aspect ratio. I don't know the idea behind this; lift distribution is not the function of aspect ratio.

The exhaust thrust is not accounted at all in the Zigrat's sheet but this is not a big problem because all compared planes had about same amount of exhaust thrust.

Quote
Originally posted by Crumpp
I recalculated the figures for 4500 ft. ASL because I do not think the table is adjusting the speeds for altitude. Here are the results.

The FW-190 is at 1.42ata @ 2700U/min as my horsepower data is much more accurate for 4500 feet. All data is calculated at 356mph the max level speed of the FW-190A8 at that altitude and power setting. This forms the base information at which the performance at lower speeds can be assessed.


Well, the question remains: Is that data true flight tested data and if it is, is filled and polished surfaces normal?

Quote
Originally posted by Crumpp
FW-190A8
Wing area S (sq. feet) - 196.98
Airplane weight, lbs (as tested) - 9418
Wing span, ft - 34.45

Step B - performance #s at a known altitude


Altitude (feet) - 4500
Maximum speed (at test alt.- mph) - 356
Engine Horsepower (bhp at test alt) - 1730
Stall speed (mph, at test alt) - 110


The power chart gives 1770 ps with RAM at 4500 ft which is 1745,79 hp. The stall speed is not really needed and unaccurate due to altitude (far too low).

Quote
Originally posted by Crumpp
Spitfire Mk IX Merlin 66 (+25) - This data represents full throttle height for the Spitfire and an easy point to calculate from. Since my data is much more complete for the FW-190 it is easier to identify the Spitfire's knowns and then establish the FW-190's performance at the same altitude. Initial data was calculated under the following known conditions:

Step A - Enter Aircraft dimension Data
Wing area S (sq. feet) - 242
Airplane weight, lbs (as tested) - 7400
Wing span, ft - 36.1

Step B - performance #s at a known altitude

Altitude (feet) - 4500
Maximum speed (at test alt.- mph) - 350
Engine Horsepower (bhp at test alt) - 2050
Stall speed (mph, at test alt) - 90


The JL 165 chart gives actually 364 mph at 4500 ft. The JL165 had MS gear high speed FTH 2800 ft with +25 lbs and the output at that altitude is about 2020 hp (according to the chart you refer). Above that altitude ouput drops about about 0,057944 hp/ft so at 4500 ft the engine output is roughly 1921 hp. It should be noted that the JF275 was about 10mph faster with the same output.

So the flat plate areas at 4500 ft are:

Fw 190A-8: 5,19 sqft (prop ef 80%, e factor 0,8)
JL165: 5,34 sqft (prop ef 80%, e factor 0,9)
JF275: 4,93 sqft

There is no need to calculate the excess power because the Spitfire has clear advantage.

Quote
Originally posted by Crumpp
If you have better data I would love to get a copy of it and will recalculate the numbers.


I have a accurate chart (among others) for the V-1650-7 which has same MS gear ratio as the Merlin 66. It lists 1940 hp without RAM at sea level with +25 lbs.

gripen

Offline Badboy

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« Reply #188 on: September 06, 2004, 04:47:58 PM »
Quote
Originally posted by gripen

The e factor in the Zigrat's sheet seems to be modeled with somekind of formula which is based on aspect ratio. I don't know the idea behind this; lift distribution is not the function of aspect ratio.
gripen


The number normally represented by the character e in induced drag calculations was originally known as Oswald’s efficiency factor, and his original paper is available for download from the NACA report server. More commonly it has a component of parasite drag lumped in with it and is just called the airplane efficiency factor and can be estimated depending on the aspect ratio, taper ratio, sweep angle and twist. Theoretically an elliptical wing would have an efficiency factor of 1, meaning that it will have a coefficient of induced drag close to the theoretical maximum. Even though it is a function of aspect ratio, sweepback angle, taper ratio and twist, the largest influence on the wing of a WWII fighter with very little sweep or twist comes from aspect ratio and taper ratio and so there are approximate formulae for estimating e that only include aspect and taper ratio, and even more approximate methods that only include aspect ratio. The important thing you must appreciate is that they are only approximate. But better than just assuming a constant value for every aircraft.  

Hope that helps...

Badboy

Edit:

Just checked my own teaching notes, and should add that the Oswald efficiency factor is also a function of wing camber and Mach number. In any case, calculating the Oswald efficiency factor from wing geometry is problematic. The values obtained are generally only valid for low AoA work because the calculations require that the flow remains fully attached, whereas in practice that is rarely the case. Generally such methods produce optimistic results.
« Last Edit: September 06, 2004, 05:00:29 PM by Badboy »
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Offline Nashwan

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« Reply #189 on: September 06, 2004, 05:04:24 PM »
Quote
Nashwan, how come that you suddenly forget your own mother language in such times? Have you forgotten how to read?

JL 165`s report notes :

"New tropical pattern air intake without gauze, but blanking plate installed.
No ice guard fitted in air intake. "


My mistake, I haven't read the full test for some time.

Quote
By the time A&AEE tested it, JL 165 was 12 mph slower at sea level, and had lost hundreds of ft/min in climb rate

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

Typical Naswhan crap vs. facts type engagement.

Facts :
In october, with R-R`s tests, on +25lbs 362mph was measured on JL 165 at 2000ft.
A few months later, with A&AEEreached 360 mph at 2000ft with JL 165 on +25lbs.


I was talking about 18 lbs performance at sea level, but nice switch there.

Quote
So we are supposed to believe JF 934 with low altitude Merlin 66 could outlcimb the 300 lbs lighter Mk IX with high altitude Merlin 70?


At low altitude, yes, at high altitude no.

JF 934 climbed at 2200ft/min at 30,000ft. BS 551 did 2600 ft/min at 30,000ft, Bs 310 2240 ft/min, EN 524 2275 ft/min.

At 25,000ft, JF 934 did 2880 ft/min, BS 551 did 3440 ft/min, EN 524 did 3050 ft/min, BS 310 did just over 3000 ft/min.

In other words, all 3 HF IXs outclimbed JF 934 at high alt.

What you are trying to do, Isegrim, is discredit the test of the serial production JF 934 by comparing it with the worst tests you can find. Therefore, if JF 934 did better than the worst Spit HF IX at high level, the test of JF 934 must be wrong.

It doesn't follow, of course, because an average Spit LF could certainly outcllimb a poor HF, even at high altitude.

Quote
Bark as desperately you want Nash1. Bull**** 543 and Bull**** 551 were experimental planes, rigged in a fashion no serial Spits were.


Here we go with the circular logic. Rather than look at the fact that the test of JF 934 fits nicely with BS 543 and 551, BS 543 and 551 are rejected. JF 934 is then compared with a different Spitfire, which it outperforms, so JF 934 is also rejected.

In fact, whilst most people would look at a series of tests and assume the one in the middle is closest to average, Isegrim rejects every test better than the worst, on the logic that it must be wrong because it's better than the worst.

Unless it's for the 109, or any other German aircraft, in which case any tests worst than the best is rejected, purely because it's worse than the best.

Isegrim, you have for some years claimed JL 165 was the most representitive Merlin 66 Spit you could find. You have now claimed that it's not representitive at all, and the estimates are based on faulty calculation.

What are you going to put on your little graph now?

Quote
Luckily now new and accurate data, actually tested is available for the JL 165 at +18. It matches well other testing at +18lbs, and can be viewed as representative for serially produced Spits.


This is going to be good.

JL 165, as tested by RR, using estimated climb figures, with a guesstimate knocked off to provide a reduction due to the radiators being partly closed, rather than actual tested data.

Quote
Hmm, I would, provided the new and better JL 165 data was for Open radiators, which unfurtanately isn`t, and closed rads are hardly conform testing with the RAF, or any other airforce.


What was the German testing procedure? I thought, and you have claimed, standard German climb tests were carried out with half open radiators.

Spit IX radiators had an exit area of 1.47 sq/ft port, 1.67 sq ft starboard, when fully open, 0.83 port and 0.83 starboard when "closed".

That makes "closed" radiators on the Spit slightly more than half open, and very comparable to 109 tests.

So under the new figures you want to use from RR, Spit IX climb rate, in a comparable condition to the 109, was 4960 ft/min at sea level, 4970 at 5,000ft, dropping to 4280 ft/min by 10,000ft, 4280 ft/min at 15,000ft.

I look forward to seeing it on the 109 climb chart :)

 
Quote
Hmm, I would, provided the new and better JL 165 data was for Open radiators, which unfurtanately isn`t, and closed rads are hardly conform testing with the RAF, or any other airforce.


Half open do though, don't they? They conform to the Luftwaffe standard, don't they? At least that's what you've always claimed in the past.

Quote
BTW, is that climb graph so irritating?


Not at all. I just don't like seeing someone going around claiming to be an authority and posting what he knows are at best flawed comparisons, and closer to outright deceptions.

Your graph is about as irritating as Luft 46, sadly it's neither as informative or as believable.
« Last Edit: September 06, 2004, 05:06:49 PM by Nashwan »

Offline Angus

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« Reply #190 on: September 06, 2004, 06:54:41 PM »
I second your opinion on izzi's graph. Bloody Frustrating comparing a fast 109G serieas aircraft to LF +18's especially at altitude.
Just as bloody typical as the famous over the nose view of the squarehead hype :D
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 MiloMorai

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« Reply #191 on: September 06, 2004, 07:34:54 PM »
Angus, take a look in my 'Need a laugh?' thread.;) Would make a good sig if it was not so large..

Offline Crumpp

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« Reply #192 on: September 06, 2004, 08:10:06 PM »
Quote
After some crosschecking I found out that there appear to be a conversion error in the Zigrat's sheet; AFAIK one mile is 5280 ft and Zigrat's uses 5350 for mph to ft/s conversion.


Your correct and I changed it.  Raises the speed to 310mph were the FW-190 gains advantage over the Spitfire in drag.

Quote
The e factor in the Zigrat's sheet seems to be modeled with somekind of formula which is based on aspect ratio. I don't know the idea behind this; lift distribution is not the function of aspect ratio.


See Badboys explaination.

http://www.aerospaceweb.org/question/aerodynamics/q0184.shtml

Seems much more accurate than an arbitrary "e" factor.

Quote
With these modifications Zigrat's spreadsheet gives same values with good enough accuracy (several decimals).


Yep and with those changes at 300mph the total drag is within 20 pounds.  At 315mph the difference increases and continues to rise the faster you go in the FW-190's favour.  No way around it, even with your values the FW-190 produced less parasitic drag than the spitfire.

Seems to me that the FW-190 has the same amount of braking forces applied to a lot more inertia.

I also emailed Zigrat to see what is up with his density.  I changed one of my spreadsheets to reflect the formula you posted.

I will check my calculations and post them in the morning.

Quote
The power chart gives 1770 ps with RAM at 4500 ft which is 1745,79 hp. The stall speed is not really needed and unaccurate due to altitude (far too low).


Agree on the stall speed.  Wasn't sure what it was at altitude for either plane so I just used the IAS values.

On the Horsepower 3 things:

1.  Horsepower varies from engine to engine within the same type of engine.  It is not an exact value.

2.  You are only talking a 15 Hp difference.

3.  1770PS is at full throttle height and the FW-190 is not at full throttle height but rather just below it.  
I will check the chart again but 13000 feet is 3.96 Km and not 5 Km which is roughly the full throttle height of the BMW-801D2 RAM at 1.42ata @ 2700U/min.

Quote
Well, the question remains: Is that data true flight tested data and if it is, is filled and polished surfaces normal?


Yes, actually that was a quite common practice for both Axis and Allied.  There is one story of a 109 pilot who crashed twice in one week.  His crew chief refused to polish anymore planes for him to he could prove he would not crash them.

Many a crew chief on both sides stayed up late at night with some turtle wax and a buffer (in the form of a lesser ranking ground crew member).

I have at least 3 flight graphs for the FW-190A8.  All of them are within a few miles per hour, one is faster, the other two are the same.  This graph is about average.

All of them including this one were performed as part of the FW-190D / Ta-152 development and testing.  Get a copy of:

http://www.schifferbooks.com/newschiffer/book_template.php?isbn=0764318764

It listed this flight as part of the program.  

Quote
The JL 165 chart gives actually 364 mph at 4500 ft. The JL165 had MS gear high speed FTH 2800 ft with +25 lbs and the output at that altitude is about 2020 hp (according to the chart you refer). Above that altitude ouput drops about about 0,057944 hp/ft so at 4500 ft the engine output is roughly 1921 hp. It should be noted that the JF275 was about 10mph faster with the same output.


And that was corrected and recalculated.  The results were the same.  The FW-190 moves to advantage over the spitfire in level speed due to having less parasitic drag.  It also goes almost as fast with a lot less power.  

The numbers are listed above.  I will recalculate them using your changes.  However, since I have already done the Merlin 61 vs FW-190A5, I am pretty sure the results will be pretty close.

Crumpp

Offline Angus

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« Reply #193 on: September 06, 2004, 08:56:36 PM »
Looking at the 190 and then the Spitty, I'd have thought they (as well as the 109) have very little difference in parasite drag.
Well, the 190 has a radial engine, which makes a lot of drag, but the rest is extrordinarily sleek ;)
Anyway, the 190 would then have more induced drag at low speeds, crossing over at high speeds, total drag being lower at high speeds right?

Anyway, nice links you're popping up with Crumpp.
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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« Reply #194 on: September 06, 2004, 10:29:24 PM »
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Looking at the 190 and then the Spitty, I'd have thought they (as well as the 109) have very little difference in parasite drag.


Kurt Tank did a great cowling job on the 190A.  If you check out the surface area of the Spitfire Mk IX's radiators it is roughly the same surface area as the intake on the FW-190's cowling.  Since the Spitfire Mk IX apparently had some boundary layer separation on the inside ducting that was never corrected that definitely accounts for the parasitic drag.  Add it the fact that the FW-190 just had much less surface area dimensionally and it just makes sense.

In fact the FW-190 has less parasitic drag throughout the flight envelope.

In a zoom climb induced drag is not a big factor as Thrust takes over for lift.  With the 190's lower parasitic drag and greater inertia it's easy to see why there is so much anecdotal evidence that Merlin Power Spits never took on 190A's in the vertical.

It seems the 190A was very efficient at converting Altitude to Speed and back.

Even with Gripen changes the numbers add up to the FW-190 having the advantage in level speed drag.  Took me a while to make the changes on the spreadsheet and copy it.  I quickly calculated an FW-190A5 and the Merlin 61 but need to research my values since so much has changed over the original ones.  You guys keep coming up with new data each post!  Lots of wiggling going on! :p  


He is correct on the Feet per second error but I am not so sure on the density.  I am waiting to hear from the guy who made the spreadsheet to see if what he using.   All in All it seems a very detailed and well put together tool.  
Here is a nice one too for calculating density:

http://www.aerospaceweb.org/design/scripts/atmos.shtml

That spreadsheet seems to use the Line lift producing theory to generate it's values.  Some of the formulas are the same, however some are different.  There are more that one theory on the creation of lift and more than one formula to determine Co-efficients.

http://www.aerospaceweb.org/question/aerodynamics/q0005.shtml

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

http://www.aerospaceweb.org/question/aerodynamics/q0015b.shtml

http://www.aerospaceweb.org/question/aerodynamics/q0136.shtml

So the values might not match exactly.

Crumpp