GIII BL45 AIRFOIL (giiib-il)
GIII BL45 AIRFOIL - Grumman/Gulfstream GIII transonic airfoils
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(giiib-il) GIII BL45 AIRFOIL Grumman/Gulfstream GIII transonic airfoils Max thickness 10.4% at 39.7% chord. Max camber 0.8% at 24.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GIII BL45 AIRFOIL
26. 26.
0.0000000 0.0000000
0.0046074 0.0083271
0.0070077 0.0104403
0.0118404 0.0139881
0.0240153 0.0208820
0.0485349 0.0310679
0.0731749 0.0386995
0.0979099 0.0443156
0.1475888 0.0511177
0.1974008 0.0550961
0.2472796 0.0576576
0.2972030 0.0592712
0.3471764 0.0598273
0.3972152 0.0589964
0.4473009 0.0571677
0.4974333 0.0543512
0.5475962 0.0508862
0.5977888 0.0467926
0.6480066 0.0421602
0.6982519 0.0369491
0.7485273 0.0310994
0.7988323 0.0246211
0.8491326 0.0182426
0.8994196 0.0121434
0.9497011 0.0061640
0.9999826 0.0001846
0.0000000 0.0000000
0.0053699 -.0078468
0.0079528 -.0096050
0.0130837 -.0123831
0.0258169 -.0173327
0.0511254 -.0238795
0.0763378 -.0283908
0.1014939 -.0317048
0.1517062 -.0362174
0.2018531 -.0393432
0.2519633 -.0416907
0.3020458 -.0434495
0.3521048 -.0447095
0.4021417 -.0455005
0.4521554 -.0458025
0.5021288 -.0452465
0.5520523 -.0436329
0.6019396 -.0412509
0.6517976 -.0382504
0.7016284 -.0346711
0.7514335 -.0305431
0.8012068 -.0257465
0.8509412 -.0201218
0.9006511 -.0139783
0.9503414 -.0074157
1.0000000 -.0001846
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Polars for GIII BL45 AIRFOIL (giiib-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiib-il | 50,000 | 9 | 28.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiib-il | 50,000 | 5 | 29.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiib-il | 100,000 | 9 | 41.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiib-il | 100,000 | 5 | 39.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiib-il | 200,000 | 9 | 52.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiib-il | 200,000 | 5 | 50.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiib-il | 500,000 | 9 | 68.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiib-il | 500,000 | 5 | 61.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiib-il | 1,000,000 | 9 | 76.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiib-il | 1,000,000 | 5 | 70.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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