GOE 795 AIRFOIL (goe795-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 795 AIRFOIL (goe795-il) Reynolds number: 500,000 Max Cl/Cd: 95.72 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe795-il-500000.txt Download as CSV file: xf-goe795-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3681 0.09266 0.09049 -0.0308 1.0000 0.0267
-6.000 -0.4549 0.02545 0.02144 -0.0472 0.9865 0.0242
-5.750 -0.4275 0.02151 0.01696 -0.0482 0.9836 0.0235
-5.500 -0.3981 0.01877 0.01378 -0.0489 0.9811 0.0230
-5.250 -0.3728 0.01639 0.01101 -0.0485 0.9763 0.0221
-5.000 -0.3418 0.01469 0.00901 -0.0491 0.9733 0.0217
-4.750 -0.3084 0.01344 0.00757 -0.0502 0.9710 0.0216
-4.500 -0.2734 0.01247 0.00647 -0.0517 0.9693 0.0219
-4.250 -0.2464 0.01175 0.00567 -0.0514 0.9633 0.0224
-4.000 -0.2129 0.01113 0.00498 -0.0526 0.9600 0.0235
-3.750 -0.1769 0.01062 0.00439 -0.0542 0.9578 0.0260
-3.500 -0.1405 0.00995 0.00368 -0.0559 0.9560 0.0323
-3.250 -0.1115 0.00959 0.00327 -0.0560 0.9496 0.0407
-3.000 -0.0756 0.00917 0.00287 -0.0577 0.9463 0.0528
-2.750 -0.0384 0.00879 0.00262 -0.0598 0.9433 0.0815
-2.500 -0.0069 0.00856 0.00243 -0.0605 0.9361 0.1053
-2.250 0.0293 0.00827 0.00221 -0.0623 0.9300 0.1256
-2.000 0.0598 0.00802 0.00204 -0.0628 0.9200 0.1505
-1.750 0.0906 0.00773 0.00190 -0.0634 0.9095 0.2048
-1.500 0.1192 0.00741 0.00177 -0.0636 0.8974 0.2696
-1.250 0.1449 0.00702 0.00166 -0.0632 0.8833 0.3655
-1.000 0.1667 0.00647 0.00158 -0.0620 0.8678 0.5229
-0.750 0.1828 0.00582 0.00154 -0.0592 0.8520 0.7211
-0.500 0.2871 0.00540 0.00172 -0.0757 0.8497 0.9593
-0.250 0.3268 0.00556 0.00179 -0.0781 0.8361 0.9832
0.000 0.3740 0.00567 0.00180 -0.0823 0.8216 0.9940
0.250 0.4188 0.00571 0.00171 -0.0860 0.8022 1.0000
0.500 0.4407 0.00577 0.00167 -0.0846 0.7814 1.0000
0.750 0.4631 0.00585 0.00164 -0.0833 0.7640 1.0000
1.000 0.4856 0.00592 0.00163 -0.0821 0.7465 1.0000
1.250 0.5082 0.00600 0.00163 -0.0809 0.7296 1.0000
1.500 0.5312 0.00609 0.00165 -0.0798 0.7141 1.0000
1.750 0.5538 0.00618 0.00168 -0.0785 0.6968 1.0000
2.000 0.5764 0.00629 0.00171 -0.0773 0.6776 1.0000
2.250 0.5986 0.00640 0.00175 -0.0760 0.6552 1.0000
2.500 0.6198 0.00656 0.00179 -0.0745 0.6250 1.0000
2.750 0.6412 0.00672 0.00187 -0.0730 0.5921 1.0000
3.000 0.6624 0.00692 0.00195 -0.0716 0.5581 1.0000
3.250 0.6826 0.00720 0.00205 -0.0699 0.5140 1.0000
3.500 0.7021 0.00755 0.00220 -0.0682 0.4629 1.0000
3.750 0.7214 0.00795 0.00239 -0.0665 0.4124 1.0000
4.000 0.7408 0.00839 0.00262 -0.0648 0.3652 1.0000
4.250 0.7613 0.00877 0.00287 -0.0634 0.3278 1.0000
4.500 0.7823 0.00913 0.00311 -0.0620 0.2952 1.0000
4.750 0.8027 0.00955 0.00337 -0.0606 0.2510 1.0000
5.000 0.8196 0.01025 0.00373 -0.0587 0.1791 1.0000
5.250 0.8375 0.01090 0.00415 -0.0569 0.1312 1.0000
5.500 0.8552 0.01159 0.00459 -0.0550 0.0853 1.0000
5.750 0.8750 0.01210 0.00503 -0.0535 0.0672 1.0000
6.000 0.8964 0.01248 0.00542 -0.0522 0.0607 1.0000
6.250 0.9172 0.01289 0.00581 -0.0509 0.0550 1.0000
6.500 0.9381 0.01329 0.00624 -0.0497 0.0496 1.0000
6.750 0.9587 0.01371 0.00668 -0.0484 0.0452 1.0000
7.000 0.9800 0.01406 0.00705 -0.0473 0.0390 1.0000
7.250 1.0012 0.01445 0.00732 -0.0461 0.0184 1.0000
7.500 1.0174 0.01533 0.00823 -0.0438 0.0122 1.0000
7.750 1.0344 0.01611 0.00910 -0.0417 0.0105 1.0000
8.000 1.0498 0.01700 0.01009 -0.0395 0.0094 1.0000
8.250 1.0562 0.01874 0.01203 -0.0356 0.0084 1.0000
8.500 1.0752 0.01926 0.01261 -0.0341 0.0080 1.0000
8.750 1.0909 0.02009 0.01354 -0.0321 0.0075 1.0000
9.000 1.1051 0.02106 0.01462 -0.0298 0.0071 1.0000
9.250 1.1171 0.02231 0.01600 -0.0273 0.0069 1.0000
9.500 1.1294 0.02352 0.01735 -0.0248 0.0067 1.0000
9.750 1.1405 0.02486 0.01886 -0.0222 0.0064 1.0000
10.000 1.1498 0.02613 0.02026 -0.0195 0.0061 1.0000
10.250 1.1567 0.02756 0.02183 -0.0164 0.0059 1.0000
10.500 1.1624 0.02916 0.02358 -0.0134 0.0057 1.0000
10.750 1.1636 0.03133 0.02594 -0.0100 0.0055 1.0000
11.000 1.1616 0.03390 0.02874 -0.0066 0.0054 1.0000
11.250 1.1587 0.03638 0.03145 -0.0035 0.0054 1.0000
11.500 1.1569 0.03857 0.03386 -0.0008 0.0054 1.0000
11.750 1.1496 0.04140 0.03692 0.0018 0.0054 1.0000
12.000 1.1452 0.04394 0.03969 0.0036 0.0056 1.0000
12.250 1.1326 0.04759 0.04359 0.0051 0.0056 1.0000
12.500 1.1137 0.05249 0.04883 0.0057 0.0059 1.0000
12.750 1.0974 0.05716 0.05369 0.0051 0.0058 1.0000
13.000 1.0561 0.06673 0.06370 0.0020 0.0063 1.0000
13.250 1.0326 0.07425 0.07142 -0.0020 0.0063 1.0000
13.500 1.0162 0.08122 0.07852 -0.0063 0.0062 1.0000
13.750 0.9854 0.09268 0.09019 -0.0138 0.0065 1.0000
14.000 0.9623 0.10343 0.10107 -0.0206 0.0066 1.0000
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Polar data table (+)
Polar graphs
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