OAF128 AIRFOIL (oaf128-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: OAF128 AIRFOIL (oaf128-il) Reynolds number: 50,000 Max Cl/Cd: 24.66 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf128-il-50000.txt Download as CSV file: xf-oaf128-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: OAF128 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.7262 0.07824 0.07115 -0.0033 1.0000 0.1648
-8.500 -0.7421 0.06883 0.06160 -0.0100 1.0000 0.1637
-8.250 -0.7603 0.05838 0.05072 -0.0174 1.0000 0.1633
-8.000 -0.7519 0.05299 0.04507 -0.0198 1.0000 0.1682
-7.750 -0.7371 0.04891 0.04071 -0.0215 1.0000 0.1767
-7.500 -0.7179 0.04565 0.03729 -0.0223 1.0000 0.1869
-7.250 -0.6981 0.04194 0.03325 -0.0238 1.0000 0.2007
-7.000 -0.6745 0.03988 0.03111 -0.0240 1.0000 0.2177
-6.750 -0.6495 0.03871 0.02998 -0.0235 1.0000 0.2370
-6.500 -0.6243 0.03737 0.02855 -0.0234 1.0000 0.2587
-6.250 -0.5986 0.03595 0.02700 -0.0237 1.0000 0.2811
-6.000 -0.5728 0.03561 0.02679 -0.0225 1.0000 0.3009
-5.750 -0.5467 0.03498 0.02621 -0.0216 1.0000 0.3204
-5.500 -0.5202 0.03404 0.02526 -0.0213 1.0000 0.3396
-5.250 -0.4931 0.03296 0.02413 -0.0212 1.0000 0.3586
-5.000 -0.4658 0.03187 0.02300 -0.0212 1.0000 0.3778
-4.750 -0.4383 0.03083 0.02193 -0.0212 1.0000 0.3977
-4.500 -0.4105 0.02980 0.02085 -0.0213 1.0000 0.4180
-4.250 -0.3824 0.02881 0.01983 -0.0215 1.0000 0.4397
-4.000 -0.3534 0.02779 0.01873 -0.0222 1.0000 0.4624
-3.750 -0.3267 0.02708 0.01809 -0.0217 1.0000 0.4828
-3.500 -0.3004 0.02641 0.01751 -0.0212 1.0000 0.5037
-3.250 -0.2746 0.02578 0.01698 -0.0207 1.0000 0.5250
-3.000 -0.2498 0.02521 0.01650 -0.0202 1.0000 0.5469
-2.750 -0.2272 0.02470 0.01610 -0.0196 1.0000 0.5693
-2.500 -0.2096 0.02432 0.01582 -0.0185 1.0000 0.5909
-2.250 -0.1965 0.02412 0.01570 -0.0173 1.0000 0.6112
-2.000 -0.1842 0.02406 0.01571 -0.0163 1.0000 0.6310
-1.750 -0.1700 0.02412 0.01581 -0.0159 1.0000 0.6519
-1.500 -0.1480 0.02421 0.01596 -0.0168 0.9965 0.6740
-1.250 -0.0869 0.02404 0.01585 -0.0230 0.9733 0.7061
-1.000 -0.0272 0.02385 0.01570 -0.0285 0.9511 0.7379
-0.750 0.0252 0.02368 0.01556 -0.0324 0.9284 0.7702
-0.500 0.0641 0.02361 0.01552 -0.0333 0.9054 0.8027
-0.250 0.0895 0.02359 0.01556 -0.0316 0.8817 0.8340
0.000 0.1134 0.02350 0.01550 -0.0294 0.8599 0.8693
0.250 0.1404 0.02332 0.01534 -0.0281 0.8392 0.9102
0.500 0.1912 0.02309 0.01509 -0.0311 0.8170 0.9569
0.750 0.2638 0.02303 0.01498 -0.0399 0.7885 1.0000
1.000 0.2752 0.02311 0.01493 -0.0402 0.7691 1.0000
1.250 0.3034 0.02345 0.01508 -0.0417 0.7489 1.0000
1.500 0.3331 0.02391 0.01538 -0.0425 0.7296 1.0000
1.750 0.3619 0.02444 0.01577 -0.0428 0.7109 1.0000
2.000 0.3901 0.02501 0.01621 -0.0428 0.6926 1.0000
2.250 0.4179 0.02562 0.01674 -0.0427 0.6749 1.0000
2.500 0.4454 0.02625 0.01728 -0.0424 0.6573 1.0000
2.750 0.4725 0.02689 0.01786 -0.0420 0.6402 1.0000
3.000 0.4995 0.02752 0.01842 -0.0414 0.6235 1.0000
3.250 0.5260 0.02807 0.01888 -0.0404 0.6074 1.0000
3.500 0.5531 0.02881 0.01960 -0.0400 0.5898 1.0000
3.750 0.5799 0.02958 0.02037 -0.0396 0.5718 1.0000
4.000 0.6065 0.03037 0.02116 -0.0392 0.5537 1.0000
4.250 0.6327 0.03107 0.02184 -0.0385 0.5353 1.0000
4.500 0.6587 0.03167 0.02242 -0.0375 0.5165 1.0000
4.750 0.6845 0.03214 0.02285 -0.0363 0.4974 1.0000
5.000 0.7103 0.03252 0.02318 -0.0350 0.4781 1.0000
5.250 0.7363 0.03285 0.02345 -0.0337 0.4587 1.0000
5.500 0.7620 0.03335 0.02394 -0.0327 0.4381 1.0000
5.750 0.7870 0.03413 0.02479 -0.0321 0.4153 1.0000
6.000 0.8125 0.03458 0.02524 -0.0310 0.3933 1.0000
6.250 0.8385 0.03485 0.02541 -0.0296 0.3717 1.0000
6.500 0.8649 0.03508 0.02547 -0.0281 0.3510 1.0000
6.750 0.8889 0.03623 0.02670 -0.0276 0.3280 1.0000
7.000 0.9131 0.03740 0.02790 -0.0270 0.3075 1.0000
7.250 0.9371 0.03863 0.02914 -0.0264 0.2895 1.0000
7.500 0.9603 0.04024 0.03081 -0.0259 0.2740 1.0000
7.750 0.9837 0.04177 0.03233 -0.0254 0.2608 1.0000
8.000 1.0088 0.04301 0.03349 -0.0247 0.2492 1.0000
8.250 1.0213 0.04681 0.03779 -0.0252 0.2385 1.0000
8.500 1.0439 0.04862 0.03955 -0.0246 0.2301 1.0000
8.750 1.0438 0.05417 0.04568 -0.0257 0.2232 1.0000
9.000 1.0770 0.05431 0.04551 -0.0243 0.2154 1.0000
9.250 1.0524 0.06292 0.05485 -0.0264 0.2128 1.0000
9.500 1.0044 0.07435 0.06668 -0.0309 0.2135 1.0000
9.750 0.9501 0.08732 0.07975 -0.0380 0.2161 1.0000
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Polar data table (+)
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