Need Ki84 HAYATE's data!

Discussion in 'Flight Test Data' started by Steven Que, Apr 24, 2009.

  1. Steven Que

    Steven Que Member

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    Hello guys.
    I need some data to analyse the aircraft's ability.
    Actually, that is my final exam report I have to prepare.
    Then I choose Ki84 Hayate to do my report.

    data in detail.
    about the gravity center's location. Aerodynamic center's location
    The airfoil's shape "NACA XXXX" or "NACA XXXXX"...

    Thanks. I hope someone will share me these data!
     
  2. peril

    peril New Member

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    Airfoil was NN-21, work I have done in finding a NACA equivalent is based on data for NN series from Ki-27 maru book. Whilst not definitive it is the best I have been able to achieve given the few clues in text.

    Root was 16.5%, tip 8% NN-21.

    GoG / MAC location unknown at this time.

    Estimated shape is:-

    NN-21 16.5%
    1.00000 0.00172
    0.99679 0.00253
    0.99071 0.00401
    0.98314 0.00584
    0.97449 0.00790
    0.96538 0.01005
    0.95615 0.01220
    0.94683 0.01435
    0.93747 0.01648
    0.92812 0.01858
    0.91877 0.02066
    0.90939 0.02272
    0.89998 0.02475
    0.89057 0.02677
    0.88117 0.02876
    0.87178 0.03073
    0.86238 0.03267
    0.85295 0.03459
    0.84352 0.03649
    0.83409 0.03836
    0.82465 0.04021
    0.81520 0.04205
    0.80577 0.04386
    0.79638 0.04564
    0.78698 0.04738
    0.77755 0.04912
    0.76814 0.05084
    0.75871 0.05252
    0.74925 0.05419
    0.73981 0.05585
    0.73040 0.05746
    0.72089 0.05907
    0.71141 0.06066
    0.70198 0.06221
    0.69247 0.06373
    0.68294 0.06526
    0.67352 0.06675
    0.66416 0.06818
    0.65477 0.06961
    0.64537 0.07101
    0.63590 0.07240
    0.62641 0.07376
    0.61691 0.07510
    0.60749 0.07640
    0.59798 0.07768
    0.58850 0.07895
    0.57905 0.08017
    0.56952 0.08137
    0.56003 0.08254
    0.55052 0.08368
    0.54098 0.08481
    0.53154 0.08588
    0.52202 0.08693
    0.51254 0.08795
    0.50303 0.08893
    0.49348 0.08990
    0.48403 0.09082
    0.47453 0.09170
    0.46506 0.09255
    0.45559 0.09336
    0.44611 0.09412
    0.43660 0.09486
    0.42711 0.09556
    0.41767 0.09621
    0.40821 0.09682
    0.39873 0.09739
    0.38925 0.09792
    0.37985 0.09840
    0.37043 0.09882
    0.36097 0.09920
    0.35149 0.09954
    0.34213 0.09983
    0.33269 0.10006
    0.32330 0.10024
    0.31393 0.10037
    0.30457 0.10043
    0.29518 0.10043
    0.28585 0.10038
    0.27655 0.10026
    0.26722 0.10007
    0.25793 0.09982
    0.24866 0.09950
    0.23943 0.09911
    0.23019 0.09863
    0.22099 0.09808
    0.21177 0.09746
    0.20266 0.09677
    0.19369 0.09600
    0.18496 0.09513
    0.17634 0.09411
    0.16779 0.09294
    0.15925 0.09162
    0.15082 0.09016
    0.14246 0.08853
    0.13411 0.08674
    0.12585 0.08480
    0.11770 0.08271
    0.10964 0.08045
    0.10170 0.07804
    0.09386 0.07545
    0.08616 0.07270
    0.07858 0.06977
    0.07119 0.06669
    0.06401 0.06345
    0.05701 0.06004
    0.05030 0.05650
    0.04386 0.05283
    0.03780 0.04904
    0.03209 0.04517
    0.02688 0.04127
    0.02217 0.03740
    0.01806 0.03366
    0.01456 0.03013
    0.01169 0.02688
    0.00935 0.02395
    0.00749 0.02136
    0.00599 0.01908
    0.00481 0.01708
    0.00393 0.01525
    0.00319 0.01361
    0.00245 0.01219
    0.00187 0.01087
    0.00152 0.00957
    0.00125 0.00834
    0.00099 0.00719
    0.00051 0.00621
    0.00031 0.00513
    0.00023 0.00400
    0.00014 0.00289
    0.00008 0.00178
    0.00003 0.00069
    0.00001 -0.00036
    0.00006 -0.00142
    0.00012 -0.00250
    0.00020 -0.00358
    0.00027 -0.00466
    0.00036 -0.00573
    0.00075 -0.00667
    0.00113 -0.00765
    0.00137 -0.00877
    0.00166 -0.00995
    0.00207 -0.01114
    0.00274 -0.01231
    0.00345 -0.01361
    0.00419 -0.01507
    0.00511 -0.01662
    0.00631 -0.01824
    0.00780 -0.02002
    0.00959 -0.02193
    0.01179 -0.02397
    0.01444 -0.02613
    0.01762 -0.02837
    0.02141 -0.03069
    0.02581 -0.03303
    0.03088 -0.03536
    0.03657 -0.03762
    0.04287 -0.03979
    0.04970 -0.04185
    0.05698 -0.04377
    0.06462 -0.04553
    0.07264 -0.04716
    0.08091 -0.04866
    0.08946 -0.05004
    0.09817 -0.05130
    0.10707 -0.05248
    0.11605 -0.05356
    0.12525 -0.05457
    0.13453 -0.05553
    0.14382 -0.05643
    0.15325 -0.05727
    0.16278 -0.05810
    0.17235 -0.05891
    0.18195 -0.05970
    0.19149 -0.06047
    0.20091 -0.06120
    0.21018 -0.06186
    0.21938 -0.06242
    0.22863 -0.06291
    0.23794 -0.06333
    0.24722 -0.06368
    0.25661 -0.06397
    0.26596 -0.06420
    0.27534 -0.06438
    0.28471 -0.06449
    0.29412 -0.06455
    0.30359 -0.06457
    0.31302 -0.06454
    0.32245 -0.06445
    0.33199 -0.06432
    0.34146 -0.06416
    0.35091 -0.06395
    0.36044 -0.06369
    0.36994 -0.06341
    0.37946 -0.06308
    0.38898 -0.06272
    0.39854 -0.06232
    0.40809 -0.06189
    0.41763 -0.06143
    0.42719 -0.06094
    0.43676 -0.06042
    0.44635 -0.05987
    0.45590 -0.05930
    0.46550 -0.05869
    0.47511 -0.05807
    0.48468 -0.05743
    0.49427 -0.05676
    0.50379 -0.05607
    0.51337 -0.05535
    0.52296 -0.05462
    0.53256 -0.05387
    0.54218 -0.05310
    0.55179 -0.05231
    0.56139 -0.05150
    0.57100 -0.05068
    0.58055 -0.04985
    0.59010 -0.04900
    0.59964 -0.04814
    0.60925 -0.04725
    0.61886 -0.04635
    0.62849 -0.04544
    0.63810 -0.04451
    0.64774 -0.04357
    0.65740 -0.04262
    0.66704 -0.04166
    0.67666 -0.04068
    0.68629 -0.03970
    0.69587 -0.03870
    0.70543 -0.03769
    0.71499 -0.03669
    0.72460 -0.03566
    0.73424 -0.03461
    0.74388 -0.03356
    0.75349 -0.03250
    0.76310 -0.03142
    0.77272 -0.03035
    0.78226 -0.02927
    0.79176 -0.02817
    0.80124 -0.02709
    0.81079 -0.02597
    0.82042 -0.02484
    0.83003 -0.02371
    0.83962 -0.02255
    0.84921 -0.02140
    0.85877 -0.02023
    0.86836 -0.01905
    0.87795 -0.01787
    0.88755 -0.01666
    0.89718 -0.01545
    0.90681 -0.01422
    0.91641 -0.01299
    0.92602 -0.01174
    0.93563 -0.01048
    0.94524 -0.00921
    0.95478 -0.00794
    0.96423 -0.00667
    0.97360 -0.00539
    0.98257 -0.00415
    0.99042 -0.00307
    0.99670 -0.00220
    1.00000 -0.00174
     
  3. Shinpachi

    Shinpachi Well-Known Member

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    Hi peril!
    The coordinates you have provided are applied on my CAD software.
    Thanks for such a fantastic data.
     

    Attached Files:

  4. HoHun

    HoHun Active Member

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    Hi Peril,

    Have you managed to genrate a polar from the coordinates? I've been toying around with Javafoil, but without results :-/

    Regards,

    Henning (HoHun)
     
  5. peril

    peril New Member

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    I set Javafoil polars to transition model 'xfoil after 1991'.

    I usually have no problems getting results, ensure closed trailing edge.

    If still having issues play with reducing max number of plotted points.
     
  6. Steven Que

    Steven Que Member

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    HI Peril,
    I wonder the coefficient of lift with NN-21 when AOA is 0 degree
    I can not find out the data from my program
    which have more than 300 airfoil's data
    But have no data of NN-21...

    Thanks
     
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