GIII BL86 AIRFOIL (modified line 31) (giiid-il)
GIII BL86 AIRFOIL (modified line 31) - Grumman/Gulfstream GIII transonic airfoils
| Details | Dat file | Parser | |
|
(giiid-il) GIII BL86 AIRFOIL (modified line 31) Grumman/Gulfstream GIII transonic airfoils Max thickness 9.7% at 39.8% chord. Max camber 1% at 29.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
GIII BL86 AIRFOIL (modified line 31)
26. 26.
0.0000000 0.0000000
0.0046998 0.0080942
0.0071260 0.0100842
0.0120046 0.0133551
0.0242719 0.0196300
0.0489348 0.0287146
0.0736829 0.0355023
0.0984902 0.0406923
0.1482250 0.0478366
0.1980593 0.0522947
0.2479536 0.0551350
0.2978883 0.0568869
0.3478537 0.0578098
0.3978577 0.0576943
0.4479094 0.0562904
0.4980022 0.0537782
0.5481265 0.0504171
0.5982786 0.0463070
0.6484618 0.0413581
0.6986743 0.0356203
0.7489152 0.0291135
0.7991684 0.0222772
0.8494031 0.0159402
0.8996048 0.0104920
0.9497957 0.0053334
0.9999863 0.0001847
0.0000004 -.0000100
0.0052638 -.0071147
0.0078230 -.0087098
0.0129157 -.0112109
0.0255821 -.0157012
0.0507987 -.0215460
0.0759405 -.0253736
0.1010415 -.0281027
0.1511795 -.0318333
0.2012727 -.0343555
0.2513407 -.0361987
0.3013917 -.0375826
0.3514312 -.0386568
0.4014618 -.0394914
0.4514846 -.0401163
0.5014730 -.0398125
0.5514255 -.0385400
0.6013495 -.0364986
0.6512482 -.0337781
0.7011248 -.0304584
0.7509772 -.0264896
0.8008045 -.0218418
0.8506171 -.0167945
0.9004206 -.0115076
0.9502156 -.0059910
1.0000000 -.0001847
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for GIII BL86 AIRFOIL (modified line 31) (giiid-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| giiid-il | 50,000 | 9 | 31 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiid-il | 100,000 | 9 | 45.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiid-il | 200,000 | 9 | 59.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiid-il | 500,000 | 9 | 70.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiid-il | 1,000,000 | 9 | 75.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||