OAF095 AIRFOIL (oaf095-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF095 AIRFOIL (oaf095-il) Reynolds number: 200,000 Max Cl/Cd: 82.83 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf095-il-200000-n5.txt Download as CSV file: xf-oaf095-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7091 0.04718 0.04309 -0.0670 1.0000 0.0225
-10.250 -0.6922 0.03716 0.03263 -0.0857 1.0000 0.0230
-10.000 -0.6701 0.03317 0.02833 -0.0922 1.0000 0.0238
-9.750 -0.6471 0.03004 0.02484 -0.0964 1.0000 0.0248
-9.500 -0.6232 0.02754 0.02197 -0.0992 1.0000 0.0259
-9.250 -0.5999 0.02574 0.01997 -0.1008 1.0000 0.0270
-9.000 -0.5770 0.02466 0.01881 -0.1015 1.0000 0.0282
-8.750 -0.5517 0.02349 0.01750 -0.1025 0.9993 0.0297
-8.500 -0.5161 0.02203 0.01577 -0.1055 0.9958 0.0314
-8.250 -0.4804 0.02068 0.01424 -0.1084 0.9927 0.0332
-8.000 -0.4453 0.01977 0.01324 -0.1108 0.9888 0.0355
-7.750 -0.4096 0.01885 0.01215 -0.1132 0.9852 0.0381
-7.500 -0.3739 0.01786 0.01102 -0.1155 0.9816 0.0405
-7.250 -0.3397 0.01714 0.01023 -0.1175 0.9766 0.0438
-7.000 -0.3045 0.01648 0.00942 -0.1194 0.9725 0.0474
-6.750 -0.2699 0.01574 0.00864 -0.1213 0.9679 0.0513
-6.500 -0.2368 0.01524 0.00803 -0.1227 0.9621 0.0564
-6.250 -0.2025 0.01466 0.00742 -0.1243 0.9574 0.0622
-6.000 -0.1709 0.01427 0.00692 -0.1253 0.9509 0.0690
-5.750 -0.1391 0.01382 0.00647 -0.1263 0.9447 0.0777
-5.500 -0.1079 0.01345 0.00607 -0.1271 0.9387 0.0872
-5.250 -0.0780 0.01314 0.00572 -0.1275 0.9313 0.0980
-5.000 -0.0480 0.01287 0.00542 -0.1279 0.9253 0.1098
-4.750 -0.0191 0.01263 0.00516 -0.1281 0.9173 0.1226
-4.500 0.0099 0.01243 0.00494 -0.1282 0.9110 0.1361
-4.250 0.0386 0.01224 0.00475 -0.1284 0.9029 0.1501
-4.000 0.0670 0.01207 0.00456 -0.1283 0.8961 0.1641
-3.750 0.0957 0.01191 0.00440 -0.1284 0.8881 0.1781
-3.500 0.1240 0.01177 0.00425 -0.1283 0.8810 0.1921
-3.250 0.1527 0.01163 0.00412 -0.1284 0.8729 0.2063
-3.000 0.1809 0.01151 0.00398 -0.1282 0.8654 0.2200
-2.750 0.2096 0.01140 0.00388 -0.1283 0.8570 0.2340
-2.500 0.2379 0.01130 0.00377 -0.1281 0.8494 0.2485
-2.250 0.2668 0.01122 0.00370 -0.1282 0.8413 0.2632
-2.000 0.2953 0.01115 0.00363 -0.1281 0.8340 0.2788
-1.750 0.3241 0.01108 0.00359 -0.1281 0.8258 0.2949
-1.500 0.3526 0.01103 0.00355 -0.1280 0.8183 0.3113
-1.250 0.3816 0.01099 0.00354 -0.1281 0.8102 0.3286
-1.000 0.4102 0.01095 0.00352 -0.1280 0.8029 0.3457
-0.750 0.4391 0.01093 0.00354 -0.1281 0.7948 0.3624
-0.500 0.4676 0.01091 0.00353 -0.1280 0.7871 0.3783
-0.250 0.4965 0.01090 0.00356 -0.1280 0.7785 0.3943
0.000 0.5251 0.01090 0.00358 -0.1279 0.7710 0.4104
0.250 0.5539 0.01090 0.00364 -0.1280 0.7623 0.4258
0.500 0.5823 0.01090 0.00367 -0.1278 0.7545 0.4420
0.750 0.6110 0.01091 0.00374 -0.1278 0.7443 0.4599
1.000 0.6394 0.01092 0.00380 -0.1277 0.7343 0.4790
1.250 0.6677 0.01093 0.00387 -0.1275 0.7245 0.4997
1.500 0.6963 0.01094 0.00397 -0.1275 0.7140 0.5244
1.750 0.7246 0.01094 0.00408 -0.1274 0.7033 0.5532
2.000 0.7525 0.01093 0.00417 -0.1272 0.6897 0.5868
2.250 0.7800 0.01090 0.00426 -0.1268 0.6729 0.6309
2.500 0.8061 0.01080 0.00436 -0.1261 0.6555 0.7049
2.750 0.8232 0.01036 0.00430 -0.1230 0.6391 1.0000
3.000 0.8510 0.01054 0.00439 -0.1228 0.6185 1.0000
3.250 0.8786 0.01074 0.00450 -0.1226 0.5939 1.0000
3.500 0.9058 0.01098 0.00464 -0.1222 0.5660 1.0000
3.750 0.9327 0.01126 0.00481 -0.1219 0.5338 1.0000
4.000 0.9589 0.01163 0.00501 -0.1215 0.4952 1.0000
4.250 0.9842 0.01211 0.00527 -0.1210 0.4468 1.0000
4.500 1.0078 0.01282 0.00565 -0.1203 0.3749 1.0000
5.000 1.0515 0.01483 0.00682 -0.1189 0.2258 1.0000
5.250 1.0737 0.01578 0.00748 -0.1183 0.1734 1.0000
5.500 1.0965 0.01661 0.00810 -0.1177 0.1346 1.0000
5.750 1.1194 0.01740 0.00873 -0.1170 0.1063 1.0000
6.000 1.1422 0.01816 0.00938 -0.1164 0.0872 1.0000
6.250 1.1651 0.01887 0.01005 -0.1157 0.0737 1.0000
6.750 1.2102 0.02030 0.01146 -0.1141 0.0569 1.0000
7.000 1.2316 0.02109 0.01225 -0.1131 0.0513 1.0000
7.250 1.2532 0.02182 0.01305 -0.1122 0.0469 1.0000
7.500 1.2726 0.02277 0.01398 -0.1110 0.0432 1.0000
7.750 1.2933 0.02352 0.01482 -0.1099 0.0401 1.0000
8.000 1.3128 0.02436 0.01571 -0.1087 0.0374 1.0000
8.250 1.3294 0.02546 0.01683 -0.1072 0.0354 1.0000
8.500 1.3470 0.02643 0.01790 -0.1057 0.0337 1.0000
8.750 1.3641 0.02739 0.01896 -0.1042 0.0319 1.0000
9.000 1.3804 0.02836 0.01999 -0.1026 0.0303 1.0000
9.250 1.3941 0.02951 0.02117 -0.1007 0.0289 1.0000
9.500 1.4057 0.03082 0.02257 -0.0986 0.0279 1.0000
9.750 1.4168 0.03201 0.02389 -0.0962 0.0270 1.0000
10.000 1.4274 0.03329 0.02529 -0.0939 0.0261 1.0000
10.250 1.4379 0.03460 0.02671 -0.0918 0.0251 1.0000
10.500 1.4479 0.03594 0.02813 -0.0899 0.0243 1.0000
10.750 1.4567 0.03738 0.02964 -0.0879 0.0235 1.0000
11.000 1.4633 0.03919 0.03151 -0.0859 0.0228 1.0000
11.250 1.4719 0.04089 0.03338 -0.0841 0.0222 1.0000
11.500 1.4795 0.04276 0.03545 -0.0823 0.0216 1.0000
11.750 1.4858 0.04476 0.03763 -0.0805 0.0210 1.0000
12.000 1.4910 0.04689 0.03993 -0.0788 0.0205 1.0000
12.250 1.4950 0.04913 0.04233 -0.0773 0.0201 1.0000
12.500 1.4978 0.05146 0.04481 -0.0759 0.0196 1.0000
12.750 1.4998 0.05390 0.04738 -0.0747 0.0192 1.0000
13.000 1.5007 0.05646 0.05008 -0.0737 0.0189 1.0000
13.250 1.5004 0.05924 0.05296 -0.0728 0.0185 1.0000
13.500 1.4979 0.06245 0.05628 -0.0721 0.0182 1.0000
13.750 1.4919 0.06621 0.06028 -0.0716 0.0179 1.0000
14.000 1.4839 0.07037 0.06472 -0.0715 0.0176 1.0000
14.250 1.4737 0.07498 0.06959 -0.0719 0.0174 1.0000
14.500 1.4614 0.08005 0.07491 -0.0727 0.0172 1.0000
14.750 1.4472 0.08565 0.08075 -0.0741 0.0170 1.0000
15.000 1.4313 0.09190 0.08726 -0.0762 0.0169 1.0000
15.250 1.4135 0.09886 0.09445 -0.0791 0.0168 1.0000
15.500 1.3935 0.10671 0.10255 -0.0830 0.0167 1.0000
15.750 1.3710 0.11570 0.11178 -0.0881 0.0167 1.0000
16.000 1.3448 0.12627 0.12260 -0.0947 0.0168 1.0000
16.250 1.3120 0.13972 0.13631 -0.1038 0.0169 1.0000
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