GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GRUMMAN K-2 AIRFOIL (k2-il) Reynolds number: 100,000 Max Cl/Cd: 28.89 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k2-il-100000.txt Download as CSV file: xf-k2-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GRUMMAN K-2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5959 0.09809 0.09254 -0.0202 1.0000 0.1570
-8.250 -0.5994 0.09465 0.08914 -0.0207 1.0000 0.1635
-8.000 -0.7011 0.08803 0.08269 -0.0279 1.0000 0.1677
-7.750 -0.6146 0.08657 0.08120 -0.0217 1.0000 0.1753
-7.500 -0.6566 0.08150 0.07623 -0.0241 1.0000 0.1819
-7.000 -0.6749 0.07469 0.06953 -0.0213 1.0000 0.1935
-6.750 -0.7200 0.07009 0.06485 -0.0222 1.0000 0.2041
-6.500 -0.7653 0.04938 0.04199 -0.0273 1.0000 0.0931
-6.250 -0.7488 0.04352 0.03561 -0.0260 1.0000 0.0768
-6.000 -0.7325 0.03953 0.03126 -0.0251 1.0000 0.0728
-5.750 -0.7119 0.03650 0.02721 -0.0239 1.0000 0.0682
-5.500 -0.6909 0.03354 0.02403 -0.0234 1.0000 0.0690
-5.250 -0.6688 0.03145 0.02190 -0.0228 1.0000 0.0708
-5.000 -0.6454 0.02963 0.01990 -0.0220 1.0000 0.0721
-4.750 -0.6211 0.02786 0.01793 -0.0211 1.0000 0.0729
-4.500 -0.5967 0.02633 0.01624 -0.0202 1.0000 0.0745
-4.250 -0.5721 0.02509 0.01483 -0.0192 1.0000 0.0775
-4.000 -0.5487 0.02365 0.01344 -0.0182 1.0000 0.0820
-3.750 -0.5250 0.02257 0.01242 -0.0172 1.0000 0.0873
-3.500 -0.5011 0.02146 0.01134 -0.0162 1.0000 0.0935
-3.250 -0.4768 0.02046 0.01045 -0.0157 1.0000 0.1044
-3.000 -0.4511 0.01932 0.00947 -0.0155 1.0000 0.1207
-2.750 -0.4211 0.01728 0.00826 -0.0170 1.0000 0.2040
-2.500 -0.4227 0.01649 0.01017 -0.0082 1.0000 0.6859
-2.250 -0.4122 0.01788 0.01148 -0.0021 1.0000 0.7378
-2.000 -0.4012 0.01905 0.01255 0.0035 1.0000 0.7682
-1.750 -0.3952 0.02003 0.01349 0.0105 1.0000 0.7884
-1.500 -0.3881 0.02078 0.01420 0.0170 1.0000 0.8093
-1.250 -0.3822 0.02145 0.01483 0.0237 1.0000 0.8369
-1.000 -0.3796 0.02184 0.01520 0.0315 1.0000 0.8669
-0.750 -0.3702 0.02172 0.01503 0.0379 1.0000 0.8967
-0.500 -0.3449 0.02131 0.01453 0.0396 1.0000 0.9171
-0.250 -0.3182 0.02085 0.01397 0.0399 1.0000 0.9313
0.000 -0.2847 0.02043 0.01346 0.0387 1.0000 0.9453
0.250 -0.2295 0.02013 0.01306 0.0333 1.0000 0.9571
0.500 -0.1780 0.01987 0.01273 0.0282 1.0000 0.9660
0.750 -0.1276 0.01960 0.01243 0.0232 1.0000 0.9722
1.000 -0.0894 0.01934 0.01216 0.0203 1.0000 0.9780
1.250 -0.0540 0.01912 0.01195 0.0180 1.0000 0.9835
1.500 -0.0174 0.01893 0.01180 0.0153 1.0000 0.9879
1.750 0.0163 0.01880 0.01171 0.0132 1.0000 0.9924
2.000 0.0493 0.01870 0.01168 0.0112 1.0000 0.9964
2.250 0.0771 0.01866 0.01172 0.0102 1.0000 1.0000
2.500 0.0841 0.01860 0.01174 0.0130 1.0000 1.0000
2.750 0.0903 0.01857 0.01180 0.0158 1.0000 1.0000
3.000 0.0957 0.01857 0.01189 0.0187 1.0000 1.0000
3.250 0.1268 0.01876 0.01222 0.0168 0.9951 1.0000
3.500 0.2499 0.01882 0.01262 -0.0012 0.9663 1.0000
3.750 0.3769 0.01725 0.01153 -0.0179 0.9156 1.0000
4.000 0.5185 0.01795 0.00926 -0.0347 0.2663 1.0000
4.250 0.5362 0.01868 0.00971 -0.0331 0.2192 1.0000
4.500 0.5536 0.01937 0.01018 -0.0315 0.1823 1.0000
4.750 0.5703 0.02021 0.01080 -0.0297 0.1426 1.0000
5.000 0.5874 0.02131 0.01172 -0.0278 0.1065 1.0000
5.250 0.6059 0.02253 0.01271 -0.0263 0.0874 1.0000
5.500 0.6263 0.02354 0.01373 -0.0249 0.0768 1.0000
5.750 0.6470 0.02462 0.01493 -0.0234 0.0694 1.0000
6.000 0.6668 0.02581 0.01611 -0.0221 0.0642 1.0000
6.250 0.6874 0.02719 0.01774 -0.0205 0.0610 1.0000
6.500 0.7068 0.02864 0.01931 -0.0190 0.0589 1.0000
6.750 0.7250 0.03043 0.02120 -0.0174 0.0576 1.0000
7.000 0.7407 0.03272 0.02374 -0.0153 0.0570 1.0000
7.250 0.7518 0.03484 0.02625 -0.0122 0.0567 1.0000
7.500 0.7589 0.03700 0.02885 -0.0087 0.0564 1.0000
7.750 0.7628 0.03925 0.03151 -0.0047 0.0561 1.0000
8.000 0.7637 0.04161 0.03424 -0.0005 0.0560 1.0000
8.250 0.7627 0.04409 0.03703 0.0037 0.0561 1.0000
8.500 0.7634 0.04671 0.03986 0.0074 0.0565 1.0000
8.750 0.7389 0.05303 0.04716 0.0137 0.0634 1.0000
9.000 0.7557 0.05663 0.05071 0.0140 0.0663 1.0000
9.250 0.6577 0.07926 0.07493 0.0098 0.1346 1.0000
9.500 0.6802 0.08255 0.07817 0.0106 0.1315 1.0000
9.750 0.7126 0.08904 0.08449 0.0109 0.1294 1.0000
10.000 0.6328 0.09641 0.09211 -0.0050 0.1251 1.0000
10.250 0.6306 0.10145 0.09713 -0.0096 0.1207 1.0000
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Polar data table (+)
Polar graphs
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