DRAGONFLY CANARD (drgnfly-il)
DRAGONFLY CANARD - Dragonfly Canard airfoil
| Details | Dat file | Parser | |
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(drgnfly-il) DRAGONFLY CANARD Dragonfly Canard airfoil Max thickness 19.3% at 37.6% chord. Max camber 6.6% at 40.9% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DRAGONFLY CANARD
74.0 67.0
0.0000000 0.0000000
0.0001457 0.0020791
0.0005989 0.0043226
0.0013409 0.0066716
0.0023466 0.0091410
0.0036141 0.0117609
0.0051572 0.0145612
0.0070160 0.0175760
0.0092433 0.0208453
0.0119110 0.0244164
0.0151171 0.0283474
0.0189834 0.0327004
0.0236648 0.0375507
0.0293351 0.0429706
0.0361713 0.0490064
0.0443123 0.0556434
0.0538113 0.0627835
0.0646016 0.0702568
0.0765326 0.0778690
0.0894156 0.0854478
0.1030717 0.0928688
0.1173461 0.1000490
0.1321090 0.1069300
0.1472595 0.1134707
0.1627235 0.1196449
0.1784441 0.1254346
0.1943784 0.1308288
0.2104903 0.1358162
0.2267510 0.1403919
0.2431323 0.1445470
0.2596113 0.1482752
0.2761710 0.1515715
0.2927934 0.1544291
0.3094666 0.1568438
0.3261755 0.1588125
0.3428982 0.1603344
0.3596047 0.1614033
0.3762569 0.1620161
0.3928149 0.1621598
0.4092597 0.1618164
0.4256004 0.1609678
0.4418859 0.1595972
0.4581774 0.1577047
0.4745027 0.1553063
0.4908638 0.1524111
0.5072857 0.1490139
0.5238335 0.1451140
0.5405811 0.1407256
0.5575834 0.1358796
0.5748784 0.1306111
0.5925030 0.1249652
0.6104801 0.1189999
0.6287965 0.1127943
0.6473631 0.1064491
0.6660159 0.1000650
0.6846015 0.0937368
0.7030689 0.0875234
0.7214391 0.0814578
0.7397921 0.0755411
0.7582108 0.0697446
0.7767314 0.0640372
0.7953659 0.0584011
0.8141143 0.0528190
0.8329656 0.0472762
0.8518957 0.0417615
0.8708630 0.0362789
0.8898250 0.0308382
0.9087250 0.0254544
0.9274510 0.0201603
0.9457506 0.0150235
0.9631459 0.0101742
0.9789165 0.0058041
0.9923993 0.0020880
1.0000000 0.0000000
0.0000000 0.0000000
0.0001805 -.0021814
0.0007254 -.0043563
0.0016289 -.0065105
0.0028783 -.0086312
0.0044806 -.0106863
0.0064676 -.0126248
0.0088683 -.0143915
0.0117057 -.0159566
0.0150096 -.0173100
0.0188391 -.0184784
0.0232904 -.0195358
0.0285087 -.0206030
0.0346850 -.0217715
0.0420663 -.0230410
0.0509365 -.0243420
0.0616005 -.0256040
0.0743312 -.0267916
0.0891285 -.0279337
0.1055755 -.0289830
0.1231631 -.0298795
0.1414954 -.0306087
0.1603064 -.0311991
0.1794002 -.0316631
0.1986707 -.0320168
0.2180541 -.0322683
0.2375143 -.0324307
0.2570233 -.0325080
0.2765712 -.0325062
0.2961400 -.0324295
0.3157297 -.0322787
0.3353333 -.0320599
0.3549327 -.0317761
0.3744961 -.0314273
0.3939943 -.0309987
0.4134563 -.0304722
0.4329322 -.0298456
0.4524549 -.0291260
0.4720535 -.0283253
0.4917410 -.0274584
0.5115053 -.0265464
0.5313196 -.0256013
0.5511649 -.0246262
0.5710391 -.0236260
0.5909453 -.0226027
0.6108834 -.0215655
0.6308455 -.0205211
0.6508187 -.0194718
0.6707878 -.0184254
0.6907469 -.0173861
0.7106941 -.0163568
0.7306303 -.0153385
0.7505585 -.0143333
0.7704768 -.0133430
0.7903870 -.0123678
0.8102773 -.0114096
0.8301386 -.0104724
0.8499590 -.0095623
0.8697084 -.0086753
0.8892588 -.0077757
0.9084961 -.0068145
0.9273193 -.0057571
0.9455405 -.0045867
0.9628015 -.0033160
0.9785467 -.0020097
0.9921971 -.0007620
1.0000000 0.0000000
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Polars for DRAGONFLY CANARD (drgnfly-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| drgnfly-il | 50,000 | 9 | 3.9 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| drgnfly-il | 50,000 | 5 | 5.8 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| drgnfly-il | 100,000 | 9 | 4.7 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| drgnfly-il | 100,000 | 5 | 8.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| drgnfly-il | 200,000 | 9 | 8.8 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| drgnfly-il | 200,000 | 5 | 45.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| drgnfly-il | 500,000 | 9 | 87.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| drgnfly-il | 500,000 | 5 | 104.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| drgnfly-il | 1,000,000 | 9 | 144.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| drgnfly-il | 1,000,000 | 5 | 149.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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