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| Military Aviation Discuss about the Pakistani Air Force capability, induction of fighters, changes in air force, comparison with other air forces of the world. |
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#151 (permalink) | |
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Pakistan Aeronautical Complex.... No we should again calculate TWR of JF-17!! TWR = 84400/(8620*9.807) TWR = 84400/(84536.34) TWR= 0.998
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#152 (permalink) | |
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TWR=THRUST/WEIGHT X 9.807 Weight = 17,700kg +fuel 9400kg = 27,100kg TWR=262,000/(27,100 X 9.807) TWR=262,000/(265769.7) TWR=0.98581591505728455877400621666051
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#153 (permalink) |
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guys plz stick to the topic
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#154 (permalink) |
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what do you think about gripen . does pak has any chance of getting them .
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#155 (permalink) |
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Hi
Why dont you guys discuss the details & Comparison between J-10B & SU 30MKI instead of JF-17. I think discussion on J-10B & SU-30MKI will be interesting.
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Every thing which has a beginning has an End.
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#156 (permalink) | |
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Also, the JF-17 is now in competition with Grippen so I do not see PAF going for Grippen. | |
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#157 (permalink) | |
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But we dont know the specification of FC-20, we will start another thread for discussion when we get FC-20!! | |
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#158 (permalink) | ||
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a) the difference between a cruise missile and an air to air missile. ![]() b) how to calculate Thrust to Weight ratio, according to previous posts. Advice: check Newton's Second Law, then learn about algebra. Mirage 2000C TWR = 0.91 (source http://www.military-heat.com/76/dassault-mirage-2000/) JF-17 TWR = 0.95 (earlier posts calculate 0.96) Mirage 2000C combat TWR = 0.89 (source: http://www.airtoaircombat.com/detail.asp?id=3) JF-17 combat TWR = 0.91 (source: http://www.airtoaircombat.com/detail.asp?id=111) Ironman thinks JF-17's TWR sucks even though it is better than Mirage 2000, which InAF have ~60 ![]() Please keep your trolling, I will keep my inside information, and don't type bullsh*t to me, ok? I can't join your circus, the positions are filled very nicely by you. | ||
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Last edited by hj786; 03-02-2009 at 07:25 PM. |
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#159 (permalink) | |
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Klimov :: Production :: Aircraft Program :: RD-33 family So 8300 kgf = 81.395195 knm. | |
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#160 (permalink) | |||
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Thrust X(Number of Engines/Total Weight of the Aircraf ) X Gravitational Constant. Is TWR plays a major role to compare combat competency?? so then compare it with LCA. Quote:
I just received a mail from my friend: In a hadith narrated by `Abdullah bin `Amr (pbuh), "Allah's Messenger (pbuh) neither talked in an insulting manner nor did he ever speak evil intentionally. He used to say, 'The most beloved to me among you is the one who has the best character and manners'" (Al-Bukhari). There are also so many quotes in hindu purana's too about good manners.. Everyone just says I'm proud of being a muslim or being a hindu.. How it can make him proud while not practicing it?? ... so I give up.. | |||
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Last edited by ironman; 03-03-2009 at 07:29 AM. |
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#161 (permalink) | |
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#162 (permalink) |
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BRAHMOS is not AAM but ASM
after the areal release of brahmos it will lose altitude and when it is very close to the ground then alone it will fire its engine and follow its flight profile
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#163 (permalink) | |||
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Are you sorry for trolling that JF's TWR without any payload is 0.91? Proof that this is false information: According to Pakistan Aeronautical Complex webpage Pakistan Aeronautical Complex.... The picture states: TOGW(2X Tip Missiles) 9100 kg (Take Off Gross Weight?) Max. Take Off Weight 12700 kg Internal Fuel Weight 2300 kg Max.External Stores Weight 3720 kg Looking at the Pakistan Aeronautical Complex.... page: "Weights: empty 6,411 kg (14,136 lb); Normal Take-Off Weight 9,072 kg (20,000 lb); Max Take-Off Weight 12,474 kg (27,500 lb)" Some small errors between figures on each page, nevertheless: Assuming Empty Weight = 6411 kg, internal fuel weight = 2300kg, Take off weight with no missiles = 6411 + 2300 = 8711 kg, additional weight is 9100 - 8711 = 389kg, 389/2 = 195 kg for each wing-tip missile. AIM-9 weighs about 85kg, PL-9C weighs about 115kg, so this agrees with the statement on the previous page that 9100kg includes full internal fuel and 2 wing-tip missiles. Therefore: Weight including full internal fuel + 2 missiles = 9100 * 9.81 = 89271 N Thrust depends on which claim you believe. According to PAC: RD-93 a/burner thrust = 84.4 kN = 84400 N According to Klimov website: "Principal specifications of RD-33: Full afterburning performance...: 8300 kgf" using google, 8300 kgf = 81 395.195 N TWR with full internal fuel + 2 missiles = 81395.195/89271 = 0.91 according to Klimov RD-33 principal thrust. TWR with full internal fuel + 2 missiles = 84400/89271 = 0.945 = 0.95 according to PAC's RD-93 thrust figure. Either way, ironman you said that 0.91 is with no payload, this post proves that is wrong, that TWR includes two missiles. Even then, you can't be sure what the thrust figure for RD-93 is, the Klimov website only mentions RD-33 "principal" figures. adm, something that might interest you: http://www.*********************/air...0a-25-252.html (replace stars with "sinodefenceforum") Quote:
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TWR of JF with RD-93B = ((81395.195*0.1)+81395.195)/89271 = 1.00295409 If we assume WS-13 will have 10% greater thrust than Klimov RD-33 as well, then a simple engine change gives JF a good TWR for dogfighting, whether the new engine is Russian or Chinese. If we take into account the planned weight reduction through use of carbon composites, TWR increases further. | |||
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Last edited by hj786; 03-03-2009 at 07:35 PM. |
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#164 (permalink) |
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Gentlemen,
Let me clear this confusion once and for all. Thrust-to-weight ratio is exactly what it states i.e THRUST / WEIGHT. THRUST = Force = mass m1 (in kg) and acc. a(m/s²) = m1.a (in Newtons) WEIGHT = Force = mass m2 (in kg) and acc. due to gravity g = m.g (in Newtons) According to PAC website, empty weight of JF-17 = 6,411 kg Internal Fuel = 2,300 kg therefore, Total weight = 8,711 kg Thrust of the engine = 84.4 N TWR of JF-17 = 84400/ (8711*9.8066) = 0.99 If you don't want to go into all that, then TWR is simply thrust (in kgs or lbs) / mass (in kg or lbs) If your TWR ratio (after taking drag into consideration) is greater than one, you can accelerate vertically , otherwise you can't because you will start loosing speed. For all those doubting and multiply the g instead of dividing, here's the reference. You cannot have a better reference than NASA itself Thrust to Weight Ratio |
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#165 (permalink) | |
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