OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: OAF095 AIRFOIL (oaf095-il) Reynolds number: 500,000 Max Cl/Cd: 116.77 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf095-il-500000.txt Download as CSV file: xf-oaf095-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4925 0.13255 0.13015 -0.0062 1.0000 0.0278
-11.750 -0.7994 0.05594 0.05317 -0.0511 1.0000 0.0182
-11.500 -0.8192 0.04293 0.03986 -0.0691 1.0000 0.0181
-11.250 -0.7971 0.03455 0.03121 -0.0858 1.0000 0.0185
-11.000 -0.7702 0.03109 0.02753 -0.0928 1.0000 0.0191
-10.750 -0.7444 0.02863 0.02486 -0.0971 1.0000 0.0198
-10.500 -0.7180 0.02649 0.02249 -0.1003 1.0000 0.0207
-10.250 -0.6912 0.02485 0.02058 -0.1026 1.0000 0.0213
-10.000 -0.6661 0.02198 0.01747 -0.1054 1.0000 0.0223
-9.750 -0.6420 0.02095 0.01639 -0.1061 1.0000 0.0231
-9.500 -0.6197 0.02012 0.01548 -0.1061 1.0000 0.0240
-9.250 -0.5987 0.01929 0.01453 -0.1059 1.0000 0.0250
-9.000 -0.5645 0.01851 0.01357 -0.1079 0.9982 0.0262
-8.750 -0.5284 0.01690 0.01184 -0.1110 0.9964 0.0280
-8.500 -0.4918 0.01622 0.01111 -0.1135 0.9946 0.0296
-8.250 -0.4554 0.01551 0.01029 -0.1157 0.9926 0.0314
-8.000 -0.4192 0.01454 0.00919 -0.1181 0.9902 0.0334
-7.750 -0.3831 0.01383 0.00845 -0.1204 0.9874 0.0358
-7.500 -0.3469 0.01330 0.00785 -0.1224 0.9846 0.0382
-7.250 -0.3116 0.01258 0.00702 -0.1243 0.9810 0.0409
-7.000 -0.2784 0.01206 0.00649 -0.1257 0.9757 0.0444
-6.750 -0.2456 0.01174 0.00609 -0.1267 0.9708 0.0476
-6.500 -0.2156 0.01115 0.00548 -0.1274 0.9637 0.0524
-6.250 -0.1872 0.01092 0.00519 -0.1274 0.9570 0.0570
-6.000 -0.1589 0.01051 0.00478 -0.1275 0.9494 0.0638
-5.750 -0.1318 0.01026 0.00447 -0.1272 0.9425 0.0711
-5.500 -0.1039 0.01002 0.00423 -0.1271 0.9351 0.0807
-5.250 -0.0765 0.00975 0.00397 -0.1269 0.9282 0.0926
-5.000 -0.0482 0.00952 0.00375 -0.1269 0.9211 0.1050
-4.750 -0.0204 0.00932 0.00355 -0.1268 0.9139 0.1180
-4.500 0.0077 0.00915 0.00339 -0.1267 0.9067 0.1312
-4.250 0.0358 0.00900 0.00325 -0.1266 0.8989 0.1452
-4.000 0.0641 0.00888 0.00311 -0.1265 0.8920 0.1588
-3.750 0.0929 0.00875 0.00298 -0.1265 0.8845 0.1724
-3.500 0.1213 0.00865 0.00287 -0.1264 0.8780 0.1860
-3.250 0.1505 0.00853 0.00276 -0.1266 0.8702 0.1998
-2.750 0.2084 0.00835 0.00259 -0.1267 0.8558 0.2283
-2.500 0.2371 0.00828 0.00251 -0.1266 0.8490 0.2431
-2.250 0.2666 0.00820 0.00246 -0.1268 0.8413 0.2588
-2.000 0.2955 0.00813 0.00240 -0.1269 0.8341 0.2744
-1.750 0.3249 0.00807 0.00237 -0.1270 0.8261 0.2914
-1.500 0.3538 0.00802 0.00233 -0.1271 0.8185 0.3081
-1.250 0.3832 0.00798 0.00232 -0.1272 0.8103 0.3244
-1.000 0.4122 0.00796 0.00231 -0.1272 0.8028 0.3415
-0.750 0.4415 0.00793 0.00232 -0.1274 0.7945 0.3580
-0.500 0.4705 0.00793 0.00232 -0.1274 0.7868 0.3748
-0.250 0.4997 0.00791 0.00234 -0.1275 0.7773 0.3919
0.000 0.5286 0.00792 0.00235 -0.1275 0.7681 0.4086
0.250 0.5577 0.00791 0.00237 -0.1276 0.7581 0.4248
0.500 0.5869 0.00791 0.00241 -0.1277 0.7490 0.4411
0.750 0.6157 0.00794 0.00244 -0.1277 0.7398 0.4587
1.000 0.6449 0.00793 0.00249 -0.1278 0.7284 0.4767
1.250 0.6737 0.00794 0.00252 -0.1278 0.7153 0.4957
1.500 0.7025 0.00795 0.00257 -0.1278 0.7017 0.5168
2.000 0.7602 0.00798 0.00271 -0.1279 0.6747 0.5744
2.500 0.8174 0.00783 0.00293 -0.1279 0.6417 0.7130
2.750 0.8362 0.00735 0.00291 -0.1255 0.6252 1.0000
3.000 0.8648 0.00751 0.00299 -0.1254 0.6056 1.0000
3.250 0.8930 0.00770 0.00309 -0.1254 0.5848 1.0000
3.500 0.9213 0.00789 0.00322 -0.1253 0.5605 1.0000
3.750 0.9491 0.00814 0.00336 -0.1252 0.5314 1.0000
4.000 0.9764 0.00847 0.00354 -0.1251 0.4958 1.0000
4.250 1.0030 0.00890 0.00377 -0.1249 0.4491 1.0000
4.500 1.0281 0.00960 0.00411 -0.1246 0.3728 1.0000
4.750 1.0517 0.01058 0.00462 -0.1242 0.2845 1.0000
5.000 1.0752 0.01153 0.00515 -0.1238 0.2113 1.0000
5.250 1.0991 0.01236 0.00568 -0.1233 0.1562 1.0000
5.500 1.1231 0.01313 0.00620 -0.1229 0.1141 1.0000
5.750 1.1474 0.01382 0.00671 -0.1224 0.0865 1.0000
6.000 1.1720 0.01443 0.00723 -0.1219 0.0698 1.0000
6.250 1.1965 0.01501 0.00777 -0.1213 0.0592 1.0000
6.500 1.2203 0.01566 0.00838 -0.1207 0.0517 1.0000
6.750 1.2447 0.01620 0.00891 -0.1201 0.0467 1.0000
7.000 1.2675 0.01693 0.00966 -0.1193 0.0423 1.0000
7.250 1.2915 0.01743 0.01019 -0.1186 0.0391 1.0000
7.500 1.3126 0.01829 0.01103 -0.1176 0.0358 1.0000
7.750 1.3345 0.01899 0.01180 -0.1166 0.0339 1.0000
8.000 1.3568 0.01961 0.01247 -0.1157 0.0321 1.0000
8.250 1.3782 0.02028 0.01316 -0.1147 0.0303 1.0000
8.500 1.3930 0.02168 0.01458 -0.1128 0.0283 1.0000
8.750 1.4145 0.02225 0.01523 -0.1118 0.0274 1.0000
9.000 1.4338 0.02303 0.01609 -0.1104 0.0263 1.0000
9.250 1.4523 0.02384 0.01695 -0.1090 0.0252 1.0000
9.500 1.4694 0.02472 0.01786 -0.1075 0.0243 1.0000
9.750 1.4824 0.02597 0.01915 -0.1054 0.0234 1.0000
10.000 1.4920 0.02759 0.02086 -0.1028 0.0225 1.0000
10.250 1.5069 0.02840 0.02176 -0.1009 0.0220 1.0000
10.500 1.5180 0.02937 0.02284 -0.0984 0.0213 1.0000
10.750 1.5283 0.03049 0.02406 -0.0960 0.0207 1.0000
11.000 1.5382 0.03169 0.02534 -0.0938 0.0202 1.0000
11.250 1.5477 0.03296 0.02669 -0.0917 0.0197 1.0000
11.500 1.5562 0.03436 0.02815 -0.0896 0.0192 1.0000
11.750 1.5628 0.03608 0.02994 -0.0875 0.0188 1.0000
12.000 1.5645 0.03897 0.03295 -0.0848 0.0182 1.0000
12.250 1.5703 0.04073 0.03488 -0.0829 0.0179 1.0000
12.500 1.5756 0.04253 0.03683 -0.0811 0.0176 1.0000
12.750 1.5799 0.04447 0.03893 -0.0794 0.0173 1.0000
13.000 1.5828 0.04663 0.04125 -0.0778 0.0169 1.0000
13.250 1.5844 0.04899 0.04375 -0.0764 0.0166 1.0000
13.500 1.5849 0.05155 0.04645 -0.0752 0.0162 1.0000
13.750 1.5837 0.05435 0.04939 -0.0741 0.0160 1.0000
14.000 1.5814 0.05734 0.05252 -0.0732 0.0158 1.0000
14.250 1.5782 0.06056 0.05588 -0.0726 0.0155 1.0000
14.500 1.5739 0.06396 0.05941 -0.0723 0.0153 1.0000
14.750 1.5683 0.06765 0.06323 -0.0722 0.0152 1.0000
15.000 1.5611 0.07168 0.06739 -0.0723 0.0150 1.0000
15.250 1.5518 0.07615 0.07199 -0.0728 0.0149 1.0000
15.500 1.5397 0.08127 0.07726 -0.0737 0.0147 1.0000
15.750 1.5244 0.08715 0.08331 -0.0752 0.0146 1.0000
16.000 1.5065 0.09376 0.09012 -0.0774 0.0146 1.0000
16.250 1.4860 0.10118 0.09774 -0.0804 0.0145 1.0000
16.500 1.4643 0.10930 0.10607 -0.0844 0.0145 1.0000
16.750 1.4438 0.11772 0.11468 -0.0890 0.0145 1.0000
17.000 1.4226 0.12680 0.12396 -0.0945 0.0145 1.0000
17.250 1.4012 0.13661 0.13397 -0.1009 0.0145 1.0000
17.500 1.3772 0.14797 0.14554 -0.1088 0.0146 1.0000
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