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1-Rockets Nozzle Design Mach 2.36 - Oct 20, 2018 09:39 pm

Norway

1-Nozzle Design CoOrds

'Theta_Max : 25.35634976855178' x(mm) : 0.0 , y(mm) : 304.79999999999995 x(mm) : 3.967234607640951 , y(mm) : 304.8258195818288 x(mm) : 7.933797087075955 , y(mm) : 304.90327395296623 x(mm) : 11.899015423970912 , y(mm) : 305.03234999110606 x(mm) : 15.86221783171612 , y(mm) : 305.21302582820795 x(mm) : 19.82273286524024 , y(mm) : 305.44527085420265 x(mm) : 23.779889534766426 , y(mm) : 305.7290457221778 x(mm) : 27.733017419491276 , y(mm) : 306.0643023550439 x(mm) : 31.681446781167406 , y(mm) : 306.45098395367984 x(mm) : 35.624508677570425 , y(mm) : 306.8890250065556 x(mm) : 39.56153507583098 , y(mm) : 307.3783513008312 x(mm) : 43.49185896561274 , y(mm) : 307.91887993492986 x(mm) : 47.41481447211726 , y(mm) : 308.5105193325832 x(mm) : 51.32973696889631 , y(mm) : 309.1531692583462 x(mm) : 55.23596319045278 , y(mm) : 309.8467208345787 x(mm) : 59.132831344611 , y(mm) : 310.59105655989185 x(mm) : 63.0196812246375 , y(mm) : 311.3860503290547 x(mm) : 66.8958543210931 , y(mm) : 312.23156745435955 x(mm) : 70.7606939333974 , y(mm) : 313.12746468844017 x(mm) : 74.61354528108701 , y(mm) : 314.07359024854105 x(mm) : 78.45375561474825 , y(mm) : 315.06978384223225 x(mm) : 82.28067432660583 , y(mm) : 316.1158766945662 x(mm) : 86.09365306074878 , y(mm) : 317.21169157667157 x(mm) : 89.89204582297477 , y(mm) : 318.35704283577905 x(mm) : 93.67520909023426 , y(mm) : 319.5517364266751 x(mm) : 97.44250191965624 , y(mm) : 320.7955699445768 x(mm) : 101.19328605713646 , y(mm) : 322.08833265942303 x(mm) : 104.92692604547048 , y(mm) : 323.4298055515767 x(mm) : 108.6427893320126 , y(mm) : 324.8197613489308 x(mm) : 112.340246375843 , y(mm) : 326.2579645654127 x(mm) : 116.01867075442419 , y(mm) : 327.7441715408806 x(mm) : 119.67743926972966 , y(mm) : 329.27813048240387 x(mm) : 123.31593205382586 , y(mm) : 330.85958150692204 x(mm) : 126.93353267389017 , y(mm) : 332.4882566852742 x(mm) : 130.52962823664672 , y(mm) : 334.1638800875912 x(mm) : 130.52962823664672 , y(mm) : 334.16388261015805 x(mm) : 189.3969715202288 , y(mm) : 359.2971286149248 x(mm) : 248.26431480381086 , y(mm) : 384.0524310707476 x(mm) : 307.13165808739296 , y(mm) : 408.4297899776267 x(mm) : 365.99900137097507 , y(mm) : 432.4292053355618 x(mm) : 424.8663446545571 , y(mm) : 456.05067714455305 x(mm) : 483.7336879381392 , y(mm) : 479.29420540460046 x(mm) : 542.6010312217213 , y(mm) : 502.159790115704 x(mm) : 601.4683745053034 , y(mm) : 524.6474312778637 x(mm) : 660.3357177888854 , y(mm) : 546.7571288910797 x(mm) : 719.2030610724676 , y(mm) : 568.4888829553515 x(mm) : 778.0704043560495 , y(mm) : 589.8426934706797 x(mm) : 836.9377476396317 , y(mm) : 610.818560437064 x(mm) : 895.8050909232138 , y(mm) : 631.4164838545043 x(mm) : 954.6724342067957 , y(mm) : 651.6364637230008 x(mm) : 1013.5397774903779 , y(mm) : 671.4785000425536 x(mm) : 1072.40712077396 , y(mm) : 690.9425928131623 x(mm) : 1131.274464057542 , y(mm) : 710.0287420348272 x(mm) : 1190.1418073411241 , y(mm) : 728.7369477075483 x(mm) : 1249.009150624706 , y(mm) : 747.0672098313255 x(mm) : 1307.8764939082882 , y(mm) : 765.019528406159 x(mm) : 1366.7438371918704 , y(mm) : 782.5939034320486 x(mm) : 1425.6111804754523 , y(mm) : 799.7903349089942 x(mm) : 1484.4785237590345 , y(mm) : 816.6088228369958 x(mm) : 1543.3458670426166 , y(mm) : 833.049367216054 x(mm) : 1602.2132103261986 , y(mm) : 849.1119680461679 x(mm) : 1661.0805536097807 , y(mm) : 864.7966253273382 x(mm) : 1719.947896893363 , y(mm) : 880.1033390595645 x(mm) : 1778.8152401769448 , y(mm) : 895.032109242847 x(mm) : 1837.682583460527 , y(mm) : 909.5829358771856 x(mm) : 1896.5499267441091 , y(mm) : 923.7558189625805 x(mm) : 1955.417270027691 , y(mm) : 937.5507584990313 x(mm) : 2014.2846133112732 , y(mm) : 950.9677544865383 x(mm) : 2073.1519565948556 , y(mm) : 964.0068069251016 x(mm) : 2132.0192998784373 , y(mm) : 976.6679158147209 x(mm) : 2190.8866431620195 , y(mm) : 988.9510811553964 x(mm) : 2249.7539864456016 , y(mm) : 1000.856302947128 x(mm) : 2308.621329729184 , y(mm) : 1012.3835811899157 x(mm) : 2367.4886730127655 , y(mm) : 1023.5329158837595 x(mm) : 2426.3560162963477 , y(mm) : 1034.3043070286594 x(mm) : 2485.22335957993 , y(mm) : 1044.6977546246158 x(mm) : 2544.090702863512 , y(mm) : 1054.713258671628 x(mm) : 2602.958046147094 , y(mm) : 1064.3508191696965 x(mm) : 2661.8253894306763 , y(mm) : 1073.6104361188213 x(mm) : 2720.692732714258 , y(mm) : 1082.492109519002 x(mm) : 2779.56007599784 , y(mm) : 1090.9958393702386 x(mm) : 2838.4274192814223 , y(mm) : 1099.1216256725315 x(mm) : 2897.2947625650045 , y(mm) : 1106.8694684258808 x(mm) : 2956.1621058485866 , y(mm) : 1114.239367630286 x(mm) : 3015.029449132169 , y(mm) : 1121.2313232857473 x(mm) : 3073.8967924157505 , y(mm) : 1127.845335392265 x(mm) : 3132.7641356993327 , y(mm) : 1134.0814039498387 x(mm) : 3191.631478982915 , y(mm) : 1139.9395289584686 x(mm) : 3250.498822266497 , y(mm) : 1145.4197104181546 x(mm) : 3309.3661

Norway

2-Nozzle design using Method of Characteristics

=========================================================================== input parameters to program are : =========================================================================== Testing Url : http://www.aerodynamics4students.com/moc/moc_flow.php?problem=1&alt=0&gamma=1.4&pto=500&tto=3159&mach=2.35&vplot=1&option=Display type of solution : 2-D Ideal Nozzle pressure altitude : 0 ft exhaust ratio of specific heats( Gama) : 1.4 Throat Stagnation Pressure (P_o : 500 psi or 55 Bars) Throat Stagnation Temperature (T_o :3159 Rankine ) Required Exit Mach Number (M_e : 2.35 ) Plot Variables :Mach

Norway
3-Output Variables ( Design Parameters )

MY SOLUTION (PYTHON PROGRAM ): 'Theta_Max : 25.35634976855178' 'Correction Factor M_No and A_Ratio : 1.3525486375687865' 'Average Correction Factor M_No and A_Ratio : 1.3560256263542985' 'Average Mach Number : 2.3506855717819275' 'Area Ratio [MAX] : 2.0290421867701305' 'Exit Radius [MIN] : 373.322405389545mm(1.22484 ft)' 'Exit Length [MIN] : 213.7809715202288 ( approx 1 foot )' 'Average Mass FlowRate (Kgm/sec): 182.31025184301103' 'Average Exit Velocity (m/sec): 2111.252046747817' 'Average Exit Pressure (N/m2) : 442477.81833213056' 'Average Exit Temperature (K) : -2570.489939277817' 'Average Exit Thrust (N) : 325836.3379357092'(73250.847 Ibf)

4-Conclusion

Results closely confirm to the website url http://www.aerodynamics4students.com/moc/moc_flow.php

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