OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF095 AIRFOIL (oaf095-il) Reynolds number: 50,000 Max Cl/Cd: 43.83 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf095-il-50000-n5.txt Download as CSV file: xf-oaf095-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4451 0.13198 0.12426 -0.0161 1.0000 0.0748
-11.000 -0.4414 0.12809 0.12039 -0.0178 1.0000 0.0740
-10.500 -0.4496 0.11828 0.11066 -0.0250 1.0000 0.0688
-10.250 -0.4438 0.11432 0.10671 -0.0263 1.0000 0.0684
-10.000 -0.4402 0.11020 0.10262 -0.0280 1.0000 0.0683
-9.750 -0.4405 0.10567 0.09814 -0.0306 1.0000 0.0686
-9.500 -0.4304 0.10315 0.09565 -0.0305 1.0000 0.0710
-9.250 -0.4241 0.10006 0.09259 -0.0314 1.0000 0.0727
-9.000 -0.4224 0.09618 0.08876 -0.0332 1.0000 0.0733
-8.750 -0.4229 0.09202 0.08467 -0.0353 1.0000 0.0734
-8.500 -0.4253 0.08790 0.08062 -0.0372 1.0000 0.0735
-8.250 -0.4289 0.08394 0.07676 -0.0389 1.0000 0.0740
-8.000 -0.4309 0.07974 0.07264 -0.0416 1.0000 0.0752
-7.750 -0.4349 0.07484 0.06783 -0.0453 1.0000 0.0766
-7.500 -0.4405 0.06839 0.06146 -0.0512 1.0000 0.0776
-7.250 -0.4441 0.05633 0.04926 -0.0655 1.0000 0.0786
-7.000 -0.4235 0.04212 0.03400 -0.0850 1.0000 0.0815
-6.750 -0.4062 0.04132 0.03329 -0.0840 1.0000 0.0850
-6.500 -0.3796 0.03753 0.02902 -0.0884 1.0000 0.0913
-6.250 -0.3517 0.03424 0.02527 -0.0917 1.0000 0.0968
-6.000 -0.3269 0.03265 0.02345 -0.0929 1.0000 0.1042
-5.750 -0.3004 0.03086 0.02140 -0.0944 1.0000 0.1117
-5.500 -0.2719 0.02918 0.01930 -0.0960 1.0000 0.1223
-5.250 -0.2485 0.02852 0.01868 -0.0961 1.0000 0.1315
-5.000 -0.2225 0.02764 0.01764 -0.0968 1.0000 0.1431
-4.750 -0.1963 0.02686 0.01671 -0.0974 1.0000 0.1564
-4.500 -0.1703 0.02627 0.01602 -0.0979 1.0000 0.1713
-4.250 -0.1450 0.02581 0.01545 -0.0983 1.0000 0.1866
-4.000 -0.1198 0.02547 0.01504 -0.0986 1.0000 0.2029
-3.750 -0.0815 0.02508 0.01452 -0.1013 0.9948 0.2243
-3.500 -0.0431 0.02477 0.01411 -0.1039 0.9885 0.2448
-3.250 -0.0034 0.02457 0.01387 -0.1067 0.9830 0.2657
-3.000 0.0336 0.02437 0.01356 -0.1089 0.9758 0.2874
-2.750 0.0738 0.02423 0.01337 -0.1117 0.9703 0.3088
-2.500 0.1085 0.02413 0.01325 -0.1133 0.9623 0.3294
-2.250 0.1492 0.02404 0.01307 -0.1161 0.9566 0.3538
-2.000 0.1825 0.02400 0.01303 -0.1174 0.9482 0.3745
-1.750 0.2229 0.02392 0.01289 -0.1201 0.9423 0.3992
-1.500 0.2556 0.02390 0.01289 -0.1212 0.9337 0.4209
-1.250 0.2955 0.02381 0.01279 -0.1236 0.9276 0.4458
-1.000 0.3277 0.02381 0.01283 -0.1246 0.9189 0.4685
-0.750 0.3654 0.02374 0.01278 -0.1265 0.9122 0.4952
-0.500 0.3953 0.02375 0.01289 -0.1270 0.9029 0.5199
-0.250 0.4310 0.02366 0.01290 -0.1284 0.8962 0.5492
0.000 0.4589 0.02370 0.01307 -0.1284 0.8864 0.5787
0.250 0.4933 0.02356 0.01309 -0.1294 0.8799 0.6146
0.500 0.5182 0.02360 0.01333 -0.1289 0.8697 0.6531
0.750 0.5483 0.02335 0.01337 -0.1287 0.8629 0.7092
1.000 0.5645 0.02314 0.01354 -0.1259 0.8523 0.8115
1.250 0.5909 0.02323 0.01364 -0.1257 0.8420 1.0000
1.500 0.6256 0.02346 0.01379 -0.1270 0.8342 1.0000
1.750 0.6540 0.02385 0.01414 -0.1272 0.8235 1.0000
2.000 0.6877 0.02401 0.01427 -0.1280 0.8156 1.0000
2.250 0.7157 0.02434 0.01463 -0.1280 0.8044 1.0000
2.500 0.7434 0.02468 0.01500 -0.1278 0.7933 1.0000
2.750 0.7754 0.02478 0.01514 -0.1280 0.7845 1.0000
3.000 0.8029 0.02506 0.01551 -0.1276 0.7728 1.0000
3.250 0.8296 0.02533 0.01586 -0.1271 0.7601 1.0000
3.500 0.8574 0.02545 0.01607 -0.1264 0.7470 1.0000
3.750 0.8854 0.02544 0.01616 -0.1255 0.7324 1.0000
4.000 0.9130 0.02535 0.01619 -0.1243 0.7160 1.0000
4.250 0.9403 0.02516 0.01611 -0.1228 0.6979 1.0000
4.500 0.9684 0.02480 0.01584 -0.1212 0.6781 1.0000
4.750 0.9918 0.02472 0.01589 -0.1193 0.6523 1.0000
5.000 1.0158 0.02451 0.01576 -0.1171 0.6228 1.0000
5.250 1.0390 0.02435 0.01563 -0.1149 0.5873 1.0000
5.500 1.0603 0.02440 0.01571 -0.1126 0.5432 1.0000
5.750 1.0799 0.02464 0.01583 -0.1101 0.4867 1.0000
6.000 1.0968 0.02526 0.01614 -0.1075 0.4073 1.0000
6.250 1.1078 0.02664 0.01685 -0.1046 0.3131 1.0000
6.500 1.1161 0.02862 0.01824 -0.1021 0.2389 1.0000
6.750 1.1254 0.03066 0.01991 -0.1000 0.1908 1.0000
7.000 1.1359 0.03261 0.02160 -0.0980 0.1597 1.0000
7.250 1.1483 0.03440 0.02329 -0.0961 0.1381 1.0000
7.500 1.1615 0.03614 0.02497 -0.0943 0.1223 1.0000
7.750 1.1763 0.03783 0.02667 -0.0925 0.1107 1.0000
8.000 1.1920 0.03953 0.02832 -0.0910 0.1011 1.0000
8.250 1.2116 0.04112 0.03007 -0.0896 0.0925 1.0000
8.500 1.2327 0.04288 0.03185 -0.0885 0.0859 1.0000
8.750 1.2533 0.04461 0.03373 -0.0874 0.0794 1.0000
9.000 1.2776 0.04668 0.03578 -0.0868 0.0749 1.0000
9.250 1.2990 0.04889 0.03836 -0.0858 0.0703 1.0000
9.500 1.3162 0.05100 0.04060 -0.0846 0.0663 1.0000
9.750 1.3369 0.05361 0.04322 -0.0840 0.0635 1.0000
10.000 1.3493 0.05669 0.04682 -0.0823 0.0614 1.0000
10.250 1.3566 0.05978 0.05034 -0.0804 0.0592 1.0000
10.500 1.3612 0.06272 0.05360 -0.0784 0.0571 1.0000
10.750 1.3633 0.06555 0.05665 -0.0764 0.0553 1.0000
11.000 1.3634 0.06848 0.05976 -0.0743 0.0541 1.0000
11.250 1.3621 0.07193 0.06340 -0.0724 0.0533 1.0000
11.500 1.3537 0.07588 0.06758 -0.0705 0.0528 1.0000
11.750 1.3360 0.08027 0.07233 -0.0688 0.0526 1.0000
12.000 1.3159 0.08514 0.07753 -0.0680 0.0525 1.0000
12.250 1.2938 0.09058 0.08327 -0.0682 0.0524 1.0000
12.500 1.2701 0.09669 0.08964 -0.0695 0.0525 1.0000
12.750 1.2454 0.10353 0.09672 -0.0720 0.0526 1.0000
13.000 1.2202 0.11121 0.10459 -0.0758 0.0527 1.0000
13.250 1.1266 0.13736 0.13115 -0.0963 0.0559 1.0000
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