OAF102 AIRFOIL (oaf102-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF102 AIRFOIL (oaf102-il) Reynolds number: 100,000 Max Cl/Cd: 60.59 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf102-il-100000-n5.txt Download as CSV file: xf-oaf102-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6084 0.06264 0.05764 -0.0503 1.0000 0.0324
-9.250 -0.6178 0.04889 0.04348 -0.0718 1.0000 0.0321
-9.000 -0.6059 0.04093 0.03475 -0.0830 1.0000 0.0327
-8.750 -0.5857 0.03734 0.03093 -0.0863 1.0000 0.0337
-8.500 -0.5621 0.03472 0.02809 -0.0889 1.0000 0.0351
-8.250 -0.5366 0.03238 0.02545 -0.0914 1.0000 0.0375
-8.000 -0.5096 0.02986 0.02244 -0.0937 1.0000 0.0403
-7.750 -0.4838 0.02772 0.02011 -0.0951 1.0000 0.0424
-7.500 -0.4587 0.02633 0.01863 -0.0960 1.0000 0.0450
-7.250 -0.4338 0.02507 0.01715 -0.0966 1.0000 0.0490
-7.000 -0.4101 0.02377 0.01572 -0.0970 1.0000 0.0526
-6.750 -0.3872 0.02283 0.01474 -0.0971 1.0000 0.0567
-6.500 -0.3550 0.02177 0.01350 -0.0990 0.9964 0.0634
-6.250 -0.3163 0.02071 0.01233 -0.1021 0.9906 0.0718
-6.000 -0.2770 0.01975 0.01129 -0.1053 0.9852 0.0837
-5.750 -0.2385 0.01889 0.01036 -0.1081 0.9791 0.0993
-5.500 -0.1998 0.01812 0.00959 -0.1111 0.9728 0.1193
-5.250 -0.1625 0.01755 0.00899 -0.1136 0.9658 0.1441
-5.000 -0.1253 0.01715 0.00855 -0.1159 0.9587 0.1711
-4.750 -0.0901 0.01683 0.00821 -0.1177 0.9505 0.1959
-4.500 -0.0547 0.01657 0.00791 -0.1195 0.9430 0.2198
-4.250 -0.0222 0.01639 0.00769 -0.1206 0.9336 0.2417
-4.000 0.0109 0.01624 0.00746 -0.1217 0.9257 0.2625
-3.750 0.0414 0.01612 0.00733 -0.1222 0.9159 0.2808
-3.500 0.0718 0.01603 0.00719 -0.1227 0.9071 0.2984
-3.250 0.1017 0.01595 0.00705 -0.1230 0.8984 0.3153
-3.000 0.1308 0.01589 0.00695 -0.1232 0.8891 0.3318
-2.750 0.1599 0.01583 0.00685 -0.1233 0.8815 0.3481
-2.500 0.1883 0.01579 0.00678 -0.1233 0.8718 0.3642
-2.250 0.2169 0.01575 0.00671 -0.1233 0.8642 0.3802
-2.000 0.2454 0.01573 0.00667 -0.1233 0.8553 0.3964
-1.750 0.2737 0.01570 0.00663 -0.1232 0.8474 0.4125
-1.500 0.3021 0.01568 0.00660 -0.1232 0.8389 0.4282
-1.250 0.3304 0.01566 0.00658 -0.1231 0.8309 0.4431
-1.000 0.3587 0.01564 0.00657 -0.1230 0.8231 0.4575
-0.750 0.3871 0.01564 0.00658 -0.1230 0.8155 0.4723
-0.500 0.4154 0.01563 0.00660 -0.1229 0.8081 0.4877
-0.250 0.4437 0.01564 0.00664 -0.1229 0.8010 0.5034
0.000 0.4721 0.01566 0.00669 -0.1229 0.7937 0.5198
0.250 0.5002 0.01567 0.00676 -0.1228 0.7872 0.5374
0.500 0.5284 0.01569 0.00687 -0.1227 0.7797 0.5567
0.750 0.5563 0.01569 0.00693 -0.1225 0.7735 0.5784
1.000 0.5843 0.01571 0.00709 -0.1225 0.7656 0.6020
1.250 0.6118 0.01568 0.00717 -0.1221 0.7595 0.6298
1.500 0.6390 0.01567 0.00736 -0.1219 0.7511 0.6649
1.750 0.6643 0.01554 0.00744 -0.1209 0.7447 0.7175
2.000 0.6821 0.01521 0.00752 -0.1183 0.7365 0.8513
2.250 0.7095 0.01518 0.00753 -0.1178 0.7298 1.0000
2.500 0.7388 0.01542 0.00780 -0.1182 0.7215 1.0000
2.750 0.7679 0.01560 0.00797 -0.1183 0.7148 1.0000
3.000 0.7968 0.01585 0.00830 -0.1186 0.7063 1.0000
3.250 0.8255 0.01604 0.00851 -0.1185 0.6995 1.0000
3.500 0.8540 0.01630 0.00888 -0.1187 0.6904 1.0000
3.750 0.8825 0.01648 0.00912 -0.1185 0.6825 1.0000
4.000 0.9092 0.01651 0.00921 -0.1179 0.6645 1.0000
4.250 0.9342 0.01632 0.00897 -0.1164 0.6316 1.0000
4.500 0.9589 0.01624 0.00879 -0.1150 0.5914 1.0000
4.750 0.9842 0.01637 0.00888 -0.1141 0.5498 1.0000
5.000 1.0089 0.01665 0.00904 -0.1131 0.4970 1.0000
5.250 1.0302 0.01736 0.00930 -0.1118 0.4041 1.0000
5.500 1.0418 0.01960 0.01034 -0.1099 0.2181 1.0000
5.750 1.0564 0.02168 0.01173 -0.1086 0.1199 1.0000
6.000 1.0755 0.02303 0.01289 -0.1076 0.0894 1.0000
6.250 1.0951 0.02422 0.01404 -0.1065 0.0751 1.0000
6.500 1.1138 0.02543 0.01523 -0.1053 0.0657 1.0000
7.000 1.1490 0.02791 0.01783 -0.1025 0.0545 1.0000
7.250 1.1669 0.02905 0.01908 -0.1011 0.0499 1.0000
7.500 1.1830 0.03040 0.02044 -0.0995 0.0467 1.0000
7.750 1.1983 0.03201 0.02206 -0.0978 0.0444 1.0000
8.000 1.2169 0.03335 0.02357 -0.0964 0.0417 1.0000
8.250 1.2349 0.03469 0.02499 -0.0951 0.0389 1.0000
8.500 1.2524 0.03622 0.02652 -0.0939 0.0370 1.0000
8.750 1.2724 0.03827 0.02858 -0.0929 0.0355 1.0000
9.000 1.2936 0.04009 0.03065 -0.0918 0.0341 1.0000
9.250 1.3128 0.04194 0.03274 -0.0907 0.0323 1.0000
9.500 1.3292 0.04370 0.03471 -0.0893 0.0306 1.0000
9.750 1.3446 0.04562 0.03676 -0.0880 0.0294 1.0000
10.000 1.3600 0.04794 0.03920 -0.0868 0.0286 1.0000
10.250 1.3738 0.05095 0.04241 -0.0855 0.0279 1.0000
10.500 1.3800 0.05393 0.04583 -0.0831 0.0274 1.0000
10.750 1.3801 0.05703 0.04937 -0.0803 0.0268 1.0000
11.000 1.3739 0.06009 0.05281 -0.0769 0.0262 1.0000
11.250 1.3649 0.06335 0.05641 -0.0739 0.0257 1.0000
11.500 1.3539 0.06687 0.06025 -0.0714 0.0252 1.0000
11.750 1.3411 0.07070 0.06437 -0.0696 0.0248 1.0000
12.000 1.3263 0.07495 0.06893 -0.0684 0.0245 1.0000
12.250 1.3092 0.07973 0.07398 -0.0680 0.0243 1.0000
12.500 1.2895 0.08518 0.07970 -0.0684 0.0242 1.0000
12.750 1.2665 0.09150 0.08626 -0.0698 0.0242 1.0000
13.000 1.2406 0.09884 0.09387 -0.0725 0.0243 1.0000
13.250 1.2114 0.10754 0.10282 -0.0769 0.0246 1.0000
13.500 1.1789 0.11821 0.11372 -0.0834 0.0250 1.0000
13.750 1.1440 0.13173 0.12742 -0.0927 0.0257 1.0000
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Polar data table (+)
Polar graphs
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