OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: OAF102 AIRFOIL (oaf102-il) Reynolds number: 50,000 Max Cl/Cd: 41.75 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf102-il-50000-n5.txt Download as CSV file: xf-oaf102-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: OAF102 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4822 0.09828 0.09108 -0.0305 1.0000 0.0613
-9.250 -0.4878 0.09241 0.08530 -0.0342 1.0000 0.0616
-9.000 -0.4960 0.08606 0.07905 -0.0383 1.0000 0.0619
-8.750 -0.5068 0.07892 0.07201 -0.0434 1.0000 0.0621
-8.500 -0.5168 0.06951 0.06262 -0.0529 1.0000 0.0621
-8.250 -0.5237 0.05777 0.05064 -0.0682 1.0000 0.0621
-8.000 -0.5110 0.05446 0.04731 -0.0706 1.0000 0.0642
-7.750 -0.4979 0.04855 0.04108 -0.0771 1.0000 0.0661
-7.500 -0.4786 0.04315 0.03521 -0.0828 1.0000 0.0690
-7.250 -0.4525 0.03770 0.02887 -0.0889 1.0000 0.0745
-7.000 -0.4316 0.03607 0.02730 -0.0892 1.0000 0.0789
-6.750 -0.4066 0.03340 0.02419 -0.0910 1.0000 0.0850
-6.500 -0.3837 0.03178 0.02244 -0.0917 1.0000 0.0922
-6.250 -0.3585 0.02982 0.02008 -0.0927 1.0000 0.1011
-6.000 -0.3361 0.02876 0.01901 -0.0929 1.0000 0.1116
-5.750 -0.3128 0.02765 0.01783 -0.0933 1.0000 0.1234
-5.500 -0.2890 0.02674 0.01683 -0.0937 1.0000 0.1394
-5.250 -0.2649 0.02598 0.01595 -0.0941 1.0000 0.1579
-5.000 -0.2417 0.02554 0.01553 -0.0942 1.0000 0.1780
-4.750 -0.2179 0.02512 0.01499 -0.0945 1.0000 0.2020
-4.500 -0.1912 0.02491 0.01481 -0.0952 0.9982 0.2257
-4.250 -0.1524 0.02466 0.01447 -0.0980 0.9913 0.2545
-4.000 -0.1134 0.02448 0.01420 -0.1008 0.9846 0.2817
-3.750 -0.0752 0.02430 0.01385 -0.1033 0.9773 0.3075
-3.500 -0.0360 0.02418 0.01367 -0.1059 0.9712 0.3302
-3.250 0.0009 0.02403 0.01338 -0.1081 0.9635 0.3531
-3.000 0.0402 0.02391 0.01319 -0.1106 0.9576 0.3740
-2.750 0.0762 0.02380 0.01298 -0.1126 0.9499 0.3950
-2.500 0.1156 0.02365 0.01275 -0.1151 0.9438 0.4164
-2.250 0.1503 0.02358 0.01262 -0.1167 0.9361 0.4360
-2.000 0.1875 0.02347 0.01243 -0.1187 0.9293 0.4573
-1.750 0.2212 0.02341 0.01231 -0.1201 0.9213 0.4765
-1.500 0.2563 0.02331 0.01220 -0.1216 0.9142 0.4957
-1.250 0.2879 0.02329 0.01216 -0.1225 0.9057 0.5150
-1.000 0.3225 0.02322 0.01207 -0.1239 0.8985 0.5366
-0.750 0.3517 0.02323 0.01213 -0.1243 0.8896 0.5566
-0.500 0.3851 0.02315 0.01209 -0.1252 0.8826 0.5806
-0.250 0.4121 0.02320 0.01223 -0.1252 0.8733 0.6033
0.000 0.4441 0.02310 0.01224 -0.1257 0.8666 0.6304
0.250 0.4694 0.02318 0.01246 -0.1254 0.8571 0.6585
0.500 0.4989 0.02304 0.01250 -0.1253 0.8508 0.6931
0.750 0.5201 0.02309 0.01279 -0.1240 0.8411 0.7366
1.000 0.5412 0.02281 0.01281 -0.1219 0.8342 0.8179
1.250 0.5650 0.02290 0.01297 -0.1213 0.8242 1.0000
1.500 0.5973 0.02325 0.01325 -0.1225 0.8166 1.0000
1.750 0.6279 0.02362 0.01357 -0.1233 0.8084 1.0000
2.000 0.6571 0.02403 0.01397 -0.1238 0.8000 1.0000
2.250 0.6874 0.02435 0.01432 -0.1242 0.7922 1.0000
2.500 0.7145 0.02484 0.01485 -0.1244 0.7830 1.0000
2.750 0.7452 0.02512 0.01516 -0.1247 0.7759 1.0000
3.000 0.7707 0.02570 0.01583 -0.1246 0.7659 1.0000
3.250 0.8019 0.02590 0.01614 -0.1247 0.7595 1.0000
3.500 0.8261 0.02656 0.01693 -0.1245 0.7486 1.0000
3.750 0.8532 0.02702 0.01753 -0.1243 0.7398 1.0000
4.000 0.8814 0.02738 0.01807 -0.1241 0.7311 1.0000
4.250 0.9060 0.02799 0.01886 -0.1237 0.7203 1.0000
4.500 0.9341 0.02829 0.01935 -0.1232 0.7111 1.0000
4.750 0.9612 0.02823 0.01949 -0.1220 0.6966 1.0000
5.000 0.9862 0.02698 0.01834 -0.1183 0.6645 1.0000
5.250 1.0075 0.02563 0.01697 -0.1138 0.6181 1.0000
5.500 1.0276 0.02520 0.01661 -0.1108 0.5718 1.0000
5.750 1.0471 0.02511 0.01656 -0.1081 0.5134 1.0000
6.000 1.0626 0.02545 0.01638 -0.1045 0.3924 1.0000
6.250 1.0612 0.02826 0.01769 -0.1005 0.2101 1.0000
6.500 1.0647 0.03110 0.01988 -0.0980 0.1460 1.0000
6.750 1.0725 0.03336 0.02188 -0.0959 0.1212 1.0000
7.000 1.0823 0.03532 0.02379 -0.0937 0.1064 1.0000
7.250 1.0929 0.03716 0.02564 -0.0917 0.0954 1.0000
7.500 1.1066 0.03885 0.02747 -0.0897 0.0876 1.0000
7.750 1.1208 0.04065 0.02918 -0.0879 0.0808 1.0000
8.000 1.1432 0.04210 0.03088 -0.0867 0.0738 1.0000
8.250 1.1700 0.04386 0.03255 -0.0860 0.0689 1.0000
8.500 1.1996 0.04569 0.03466 -0.0855 0.0636 1.0000
8.750 1.2261 0.04773 0.03685 -0.0850 0.0593 1.0000
9.000 1.2552 0.05034 0.03947 -0.0850 0.0567 1.0000
9.250 1.2769 0.05322 0.04274 -0.0841 0.0542 1.0000
9.500 1.2918 0.05608 0.04605 -0.0826 0.0516 1.0000
9.750 1.3045 0.05908 0.04940 -0.0811 0.0496 1.0000
10.000 1.3147 0.06242 0.05312 -0.0795 0.0484 1.0000
10.250 1.3210 0.06589 0.05691 -0.0777 0.0476 1.0000
10.500 1.3230 0.06940 0.06071 -0.0758 0.0468 1.0000
10.750 1.3226 0.07292 0.06446 -0.0738 0.0460 1.0000
11.000 1.3198 0.07688 0.06854 -0.0720 0.0452 1.0000
11.250 1.3014 0.08049 0.07251 -0.0690 0.0449 1.0000
11.500 1.2820 0.08465 0.07700 -0.0671 0.0448 1.0000
11.750 1.2615 0.08933 0.08197 -0.0662 0.0447 1.0000
12.000 1.2400 0.09456 0.08746 -0.0664 0.0447 1.0000
12.250 1.2182 0.10034 0.09348 -0.0676 0.0447 1.0000
12.500 1.1963 0.10670 0.10004 -0.0698 0.0448 1.0000
12.750 1.1749 0.11363 0.10715 -0.0729 0.0450 1.0000
13.000 1.1544 0.12113 0.11479 -0.0769 0.0451 1.0000
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Polar data table (+)
Polar graphs
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