OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: OAF095 AIRFOIL (oaf095-il) Reynolds number: 100,000 Max Cl/Cd: 65.67 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf095-il-100000.txt Download as CSV file: xf-oaf095-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: OAF095 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3803 0.09436 0.08932 -0.0278 1.0000 0.1418
-8.000 -0.3783 0.09168 0.08669 -0.0291 1.0000 0.1469
-7.750 -0.4161 0.09070 0.08596 -0.0381 1.0000 0.1508
-7.500 -0.4032 0.08641 0.08168 -0.0330 1.0000 0.1522
-7.250 -0.4471 0.06126 0.05651 -0.0612 1.0000 0.0949
-7.000 -0.4411 0.05993 0.05522 -0.0584 1.0000 0.0958
-6.750 -0.4185 0.04221 0.03674 -0.0810 1.0000 0.0916
-6.500 -0.3737 0.03209 0.02514 -0.0947 1.0000 0.0943
-6.250 -0.3522 0.03029 0.02345 -0.0949 1.0000 0.0987
-6.000 -0.3231 0.02812 0.02083 -0.0970 1.0000 0.1055
-5.750 -0.2933 0.02587 0.01824 -0.0990 1.0000 0.1116
-5.500 -0.2653 0.02476 0.01680 -0.1000 1.0000 0.1209
-5.250 -0.2391 0.02373 0.01577 -0.1005 1.0000 0.1292
-5.000 -0.2116 0.02289 0.01478 -0.1013 1.0000 0.1410
-4.750 -0.1830 0.02214 0.01389 -0.1021 1.0000 0.1544
-4.500 -0.1558 0.02170 0.01340 -0.1027 1.0000 0.1698
-4.250 -0.1290 0.02135 0.01303 -0.1032 1.0000 0.1861
-4.000 -0.1029 0.02115 0.01282 -0.1036 1.0000 0.2033
-3.750 -0.0772 0.02104 0.01270 -0.1039 1.0000 0.2213
-3.500 -0.0514 0.02098 0.01259 -0.1043 1.0000 0.2399
-3.250 -0.0161 0.02089 0.01251 -0.1064 0.9970 0.2609
-3.000 0.0274 0.02084 0.01250 -0.1099 0.9916 0.2848
-2.750 0.0710 0.02075 0.01239 -0.1133 0.9857 0.3084
-2.500 0.1131 0.02072 0.01240 -0.1164 0.9795 0.3312
-2.250 0.1561 0.02065 0.01232 -0.1197 0.9731 0.3550
-2.000 0.1963 0.02063 0.01236 -0.1224 0.9662 0.3775
-1.750 0.2375 0.02058 0.01232 -0.1252 0.9593 0.4024
-1.500 0.2760 0.02057 0.01239 -0.1275 0.9522 0.4266
-1.250 0.3154 0.02050 0.01240 -0.1299 0.9450 0.4522
-1.000 0.3561 0.02045 0.01239 -0.1325 0.9386 0.4798
-0.750 0.3921 0.02040 0.01246 -0.1342 0.9307 0.5051
-0.500 0.4388 0.02018 0.01235 -0.1378 0.9265 0.5352
-0.250 0.4682 0.02023 0.01251 -0.1383 0.9164 0.5610
0.000 0.5108 0.01998 0.01240 -0.1408 0.9113 0.5935
0.250 0.5381 0.02006 0.01262 -0.1408 0.9010 0.6242
0.500 0.5774 0.01976 0.01249 -0.1424 0.8955 0.6662
0.750 0.6019 0.01974 0.01271 -0.1415 0.8845 0.7120
1.000 0.6283 0.01930 0.01265 -0.1402 0.8768 0.7957
1.250 0.6519 0.01902 0.01252 -0.1388 0.8662 1.0000
1.500 0.6830 0.01927 0.01268 -0.1395 0.8556 1.0000
1.750 0.7187 0.01918 0.01253 -0.1402 0.8487 1.0000
2.000 0.7454 0.01948 0.01282 -0.1399 0.8369 1.0000
2.250 0.7742 0.01959 0.01293 -0.1395 0.8264 1.0000
2.500 0.8059 0.01934 0.01267 -0.1389 0.8176 1.0000
2.750 0.8324 0.01931 0.01268 -0.1378 0.8041 1.0000
3.000 0.8593 0.01916 0.01256 -0.1365 0.7905 1.0000
3.250 0.8862 0.01894 0.01236 -0.1351 0.7766 1.0000
3.500 0.9130 0.01865 0.01212 -0.1334 0.7618 1.0000
3.750 0.9395 0.01830 0.01179 -0.1317 0.7456 1.0000
4.000 0.9659 0.01790 0.01140 -0.1298 0.7278 1.0000
4.250 0.9923 0.01749 0.01098 -0.1278 0.7089 1.0000
4.500 1.0170 0.01732 0.01087 -0.1261 0.6852 1.0000
4.750 1.0427 0.01704 0.01058 -0.1243 0.6607 1.0000
5.000 1.0673 0.01689 0.01043 -0.1225 0.6307 1.0000
5.250 1.0907 0.01687 0.01045 -0.1207 0.5920 1.0000
5.500 1.1131 0.01695 0.01044 -0.1188 0.5409 1.0000
5.750 1.1317 0.01745 0.01059 -0.1163 0.4513 1.0000
6.000 1.1386 0.01951 0.01147 -0.1128 0.2838 1.0000
6.250 1.1455 0.02216 0.01321 -0.1100 0.1898 1.0000
6.500 1.1593 0.02408 0.01478 -0.1079 0.1514 1.0000
6.750 1.1751 0.02583 0.01626 -0.1061 0.1309 1.0000
7.000 1.1936 0.02752 0.01778 -0.1046 0.1162 1.0000
7.250 1.2149 0.02899 0.01926 -0.1033 0.1052 1.0000
7.500 1.2378 0.03076 0.02105 -0.1023 0.0967 1.0000
7.750 1.2618 0.03272 0.02281 -0.1018 0.0892 1.0000
8.000 1.2868 0.03460 0.02494 -0.1008 0.0843 1.0000
8.250 1.3101 0.03636 0.02677 -0.1000 0.0791 1.0000
8.500 1.3355 0.03924 0.02967 -0.0997 0.0750 1.0000
8.750 1.3564 0.04161 0.03247 -0.0983 0.0728 1.0000
9.000 1.3753 0.04419 0.03542 -0.0968 0.0703 1.0000
9.250 1.3939 0.04653 0.03794 -0.0956 0.0674 1.0000
9.500 1.4117 0.04949 0.04100 -0.0947 0.0651 1.0000
9.750 1.4253 0.05418 0.04601 -0.0934 0.0641 1.0000
10.000 1.4323 0.05891 0.05115 -0.0913 0.0638 1.0000
10.250 1.4339 0.06279 0.05550 -0.0885 0.0636 1.0000
10.500 1.4302 0.06671 0.05986 -0.0854 0.0634 1.0000
10.750 1.4214 0.07071 0.06428 -0.0822 0.0632 1.0000
11.000 1.4083 0.07490 0.06882 -0.0791 0.0631 1.0000
11.250 1.3922 0.07921 0.07340 -0.0760 0.0633 1.0000
11.500 1.3764 0.08397 0.07836 -0.0735 0.0636 1.0000
11.750 1.3623 0.08830 0.08291 -0.0714 0.0641 1.0000
12.000 1.2363 0.10073 0.09621 -0.0746 0.0716 1.0000
12.250 1.2060 0.10945 0.10506 -0.0787 0.0733 1.0000
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Polar data table (+)
Polar graphs
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