GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GRUMMAN K-2 AIRFOIL (k2-il) Reynolds number: 50,000 Max Cl/Cd: 21.75 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k2-il-50000.txt Download as CSV file: xf-k2-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.6912 0.07690 0.06937 -0.0257 1.0000 0.1793
-7.000 -0.7225 0.06950 0.06174 -0.0277 1.0000 0.1601
-6.750 -0.7390 0.06321 0.05504 -0.0282 1.0000 0.1460
-6.500 -0.7477 0.05741 0.04852 -0.0282 1.0000 0.1340
-6.250 -0.7365 0.05322 0.04414 -0.0274 1.0000 0.1299
-6.000 -0.7265 0.04875 0.03910 -0.0269 1.0000 0.1248
-5.750 -0.7113 0.04506 0.03472 -0.0264 1.0000 0.1222
-5.500 -0.6920 0.04211 0.03150 -0.0258 1.0000 0.1235
-5.250 -0.6708 0.03941 0.02852 -0.0251 1.0000 0.1251
-5.000 -0.6478 0.03684 0.02562 -0.0244 1.0000 0.1261
-4.750 -0.6237 0.03456 0.02306 -0.0234 1.0000 0.1281
-4.500 -0.5991 0.03270 0.02086 -0.0225 1.0000 0.1334
-4.250 -0.5751 0.03080 0.01889 -0.0212 1.0000 0.1397
-4.000 -0.5508 0.02931 0.01737 -0.0195 1.0000 0.1477
-3.750 -0.5276 0.02796 0.01613 -0.0175 1.0000 0.1602
-3.500 -0.5050 0.02675 0.01501 -0.0151 1.0000 0.1772
-3.250 -0.4848 0.02536 0.01390 -0.0129 1.0000 0.2068
-3.000 -0.4694 0.02265 0.01234 -0.0113 1.0000 0.3056
-2.750 -0.4886 0.02477 0.01687 0.0080 1.0000 0.7215
-2.500 -0.3059 0.03169 0.02245 0.0038 1.0000 0.9247
-2.250 -0.1887 0.02924 0.01935 -0.0136 1.0000 0.9763
-2.000 -0.1092 0.02731 0.01708 -0.0256 1.0000 1.0000
-1.750 -0.0979 0.02670 0.01639 -0.0242 1.0000 1.0000
-1.500 -0.0864 0.02615 0.01579 -0.0226 1.0000 1.0000
-1.250 -0.0749 0.02566 0.01525 -0.0210 1.0000 1.0000
-1.000 -0.0632 0.02522 0.01478 -0.0193 1.0000 1.0000
-0.750 -0.0516 0.02483 0.01435 -0.0175 1.0000 1.0000
-0.500 -0.0401 0.02447 0.01398 -0.0156 1.0000 1.0000
-0.250 -0.0286 0.02415 0.01366 -0.0136 1.0000 1.0000
0.000 -0.0174 0.02386 0.01338 -0.0115 1.0000 1.0000
0.250 -0.0063 0.02360 0.01313 -0.0094 1.0000 1.0000
0.500 0.0046 0.02337 0.01293 -0.0072 1.0000 1.0000
0.750 0.0152 0.02316 0.01276 -0.0049 1.0000 1.0000
1.000 0.0255 0.02298 0.01262 -0.0026 1.0000 1.0000
1.250 0.0355 0.02282 0.01252 -0.0002 1.0000 1.0000
1.500 0.0452 0.02268 0.01245 0.0023 1.0000 1.0000
1.750 0.0544 0.02256 0.01241 0.0048 1.0000 1.0000
2.000 0.0632 0.02246 0.01239 0.0074 1.0000 1.0000
2.250 0.0716 0.02238 0.01241 0.0100 1.0000 1.0000
2.500 0.0794 0.02233 0.01246 0.0127 1.0000 1.0000
2.750 0.0868 0.02229 0.01254 0.0154 1.0000 1.0000
3.000 0.0936 0.02228 0.01265 0.0181 1.0000 1.0000
3.250 0.0998 0.02230 0.01280 0.0209 1.0000 1.0000
3.500 0.1055 0.02235 0.01300 0.0236 1.0000 1.0000
3.750 0.1108 0.02245 0.01325 0.0261 1.0000 1.0000
4.000 0.1174 0.02265 0.01362 0.0283 1.0000 1.0000
4.250 0.1267 0.02299 0.01416 0.0295 1.0000 1.0000
4.500 0.1858 0.02414 0.01573 0.0218 0.9817 1.0000
4.750 0.5474 0.02517 0.01456 -0.0233 0.2764 1.0000
5.000 0.5748 0.02684 0.01599 -0.0229 0.2209 1.0000
5.250 0.5988 0.02870 0.01761 -0.0220 0.1807 1.0000
5.500 0.6203 0.03057 0.01961 -0.0205 0.1556 1.0000
5.750 0.6403 0.03250 0.02168 -0.0188 0.1400 1.0000
6.000 0.6599 0.03464 0.02375 -0.0175 0.1292 1.0000
6.250 0.6741 0.03672 0.02644 -0.0145 0.1236 1.0000
6.500 0.6879 0.03866 0.02857 -0.0122 0.1177 1.0000
6.750 0.7006 0.04128 0.03129 -0.0100 0.1138 1.0000
7.000 0.7076 0.04385 0.03432 -0.0065 0.1132 1.0000
7.250 0.7133 0.04664 0.03746 -0.0030 0.1134 1.0000
7.500 0.7168 0.04953 0.04066 0.0004 0.1137 1.0000
7.750 0.7196 0.05257 0.04395 0.0037 0.1142 1.0000
8.000 0.6998 0.05622 0.04861 0.0093 0.1213 1.0000
8.250 0.6986 0.06039 0.05308 0.0112 0.1249 1.0000
8.500 0.7044 0.06468 0.05753 0.0120 0.1277 1.0000
8.750 0.5745 0.09202 0.08604 -0.0224 0.3599 1.0000
9.000 0.5810 0.09589 0.08988 -0.0228 0.3440 1.0000
9.500 0.5845 0.10349 0.09741 -0.0248 0.3164 1.0000
9.750 0.5856 0.10729 0.10118 -0.0261 0.3037 1.0000
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Polar data table (+)
Polar graphs
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