GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 704 AIRFOIL (goe704-il) Reynolds number: 500,000 Max Cl/Cd: 72.68 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe704-il-500000-n5.txt Download as CSV file: xf-goe704-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 704 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.0070 0.08435 0.08099 -0.0177 1.0000 0.0090
-15.250 -1.0803 0.06797 0.06443 -0.0273 1.0000 0.0087
-15.000 -1.1577 0.04559 0.04153 -0.0462 1.0000 0.0084
-14.750 -1.1745 0.04084 0.03658 -0.0474 1.0000 0.0084
-14.500 -1.1834 0.03776 0.03334 -0.0465 1.0000 0.0085
-14.250 -1.1877 0.03542 0.03085 -0.0448 1.0000 0.0086
-14.000 -1.1887 0.03350 0.02879 -0.0426 1.0000 0.0087
-13.750 -1.1873 0.03187 0.02703 -0.0401 1.0000 0.0089
-13.500 -1.1839 0.03046 0.02549 -0.0375 1.0000 0.0091
-13.250 -1.1787 0.02922 0.02413 -0.0348 1.0000 0.0093
-13.000 -1.1689 0.02805 0.02283 -0.0327 1.0000 0.0095
-12.750 -1.1562 0.02697 0.02163 -0.0309 1.0000 0.0097
-12.500 -1.1414 0.02599 0.02053 -0.0293 1.0000 0.0099
-12.250 -1.1281 0.02482 0.01926 -0.0276 1.0000 0.0103
-12.000 -1.1126 0.02376 0.01811 -0.0261 1.0000 0.0107
-11.750 -1.0949 0.02287 0.01712 -0.0248 1.0000 0.0112
-11.500 -1.0760 0.02206 0.01622 -0.0237 1.0000 0.0116
-11.250 -1.0562 0.02130 0.01538 -0.0226 1.0000 0.0121
-11.000 -1.0357 0.02060 0.01458 -0.0216 1.0000 0.0126
-10.750 -1.0145 0.01995 0.01384 -0.0207 1.0000 0.0131
-10.500 -0.9920 0.01912 0.01294 -0.0202 0.9923 0.0139
-10.250 -0.9634 0.01840 0.01214 -0.0208 0.9742 0.0149
-10.000 -0.9359 0.01779 0.01145 -0.0211 0.9561 0.0161
-9.750 -0.9115 0.01723 0.01081 -0.0206 0.9364 0.0175
-9.500 -0.8894 0.01670 0.01021 -0.0195 0.9171 0.0195
-9.250 -0.8671 0.01625 0.00966 -0.0184 0.8994 0.0218
-9.000 -0.8446 0.01579 0.00913 -0.0174 0.8827 0.0251
-8.750 -0.8212 0.01536 0.00863 -0.0166 0.8673 0.0287
-8.500 -0.7969 0.01499 0.00818 -0.0159 0.8534 0.0328
-8.250 -0.7725 0.01459 0.00773 -0.0153 0.8413 0.0376
-8.000 -0.7474 0.01424 0.00732 -0.0148 0.8302 0.0419
-7.750 -0.7221 0.01391 0.00693 -0.0143 0.8196 0.0467
-7.500 -0.6963 0.01359 0.00656 -0.0140 0.8101 0.0514
-7.250 -0.6704 0.01329 0.00622 -0.0136 0.8019 0.0572
-7.000 -0.6442 0.01298 0.00590 -0.0133 0.7938 0.0638
-6.500 -0.5910 0.01249 0.00538 -0.0129 0.7795 0.0800
-6.250 -0.5641 0.01229 0.00518 -0.0127 0.7732 0.0892
-6.000 -0.5368 0.01213 0.00499 -0.0126 0.7675 0.0962
-5.750 -0.5094 0.01197 0.00481 -0.0125 0.7614 0.1018
-5.500 -0.4818 0.01184 0.00461 -0.0124 0.7561 0.1055
-5.250 -0.4543 0.01168 0.00441 -0.0122 0.7512 0.1096
-5.000 -0.4267 0.01152 0.00425 -0.0122 0.7460 0.1141
-4.750 -0.3990 0.01140 0.00408 -0.0121 0.7411 0.1178
-4.500 -0.3711 0.01131 0.00392 -0.0121 0.7368 0.1209
-4.250 -0.3435 0.01113 0.00375 -0.0120 0.7320 0.1251
-4.000 -0.3157 0.01100 0.00360 -0.0120 0.7272 0.1292
-3.750 -0.2879 0.01090 0.00346 -0.0119 0.7230 0.1331
-3.500 -0.2597 0.01080 0.00333 -0.0119 0.7186 0.1365
-3.250 -0.2320 0.01064 0.00319 -0.0119 0.7138 0.1421
-3.000 -0.2041 0.01053 0.00306 -0.0118 0.7088 0.1467
-2.750 -0.1761 0.01044 0.00294 -0.0118 0.7021 0.1507
-2.500 -0.1484 0.01032 0.00280 -0.0117 0.6931 0.1551
-2.250 -0.1206 0.01021 0.00268 -0.0117 0.6848 0.1606
-2.000 -0.0926 0.01011 0.00257 -0.0117 0.6786 0.1662
-1.750 -0.0648 0.01001 0.00248 -0.0116 0.6733 0.1739
-1.500 -0.0367 0.00989 0.00240 -0.0116 0.6675 0.1844
-1.250 -0.0090 0.00976 0.00232 -0.0116 0.6614 0.1995
-1.000 0.0186 0.00963 0.00226 -0.0116 0.6555 0.2204
-0.750 0.0463 0.00949 0.00221 -0.0116 0.6485 0.2466
-0.500 0.0738 0.00937 0.00216 -0.0115 0.6419 0.2746
-0.250 0.1014 0.00923 0.00212 -0.0115 0.6334 0.3019
0.000 0.1287 0.00911 0.00207 -0.0114 0.6231 0.3308
0.250 0.1556 0.00898 0.00202 -0.0112 0.6084 0.3669
0.750 0.2055 0.00841 0.00192 -0.0102 0.5801 0.5234
1.000 0.2165 0.00731 0.00204 -0.0062 0.5682 0.8634
1.250 0.2443 0.00744 0.00215 -0.0060 0.5515 0.8924
1.500 0.2718 0.00759 0.00223 -0.0057 0.5312 0.9076
1.750 0.2990 0.00778 0.00233 -0.0054 0.5066 0.9190
2.000 0.3248 0.00798 0.00243 -0.0049 0.4816 0.9301
2.250 0.3525 0.00827 0.00259 -0.0048 0.4525 0.9392
2.500 0.3788 0.00858 0.00276 -0.0044 0.4201 0.9471
2.750 0.4083 0.00893 0.00297 -0.0048 0.3904 0.9534
3.000 0.4343 0.00919 0.00313 -0.0044 0.3692 0.9599
3.250 0.4701 0.00951 0.00336 -0.0061 0.3487 0.9635
3.500 0.5045 0.00982 0.00357 -0.0077 0.3294 0.9675
3.750 0.5302 0.01004 0.00373 -0.0073 0.3137 0.9720
4.000 0.5658 0.01030 0.00390 -0.0091 0.2981 0.9733
4.250 0.6025 0.01055 0.00409 -0.0113 0.2838 0.9746
4.500 0.6357 0.01077 0.00427 -0.0126 0.2707 0.9758
4.750 0.6654 0.01095 0.00441 -0.0133 0.2598 0.9769
5.000 0.6938 0.01113 0.00456 -0.0136 0.2499 0.9779
5.500 0.7489 0.01151 0.00489 -0.0140 0.2316 0.9805
5.750 0.7749 0.01172 0.00507 -0.0138 0.2237 0.9822
6.000 0.8001 0.01191 0.00526 -0.0135 0.2156 0.9839
6.250 0.8297 0.01215 0.00547 -0.0142 0.2074 0.9846
6.500 0.8594 0.01236 0.00568 -0.0149 0.2007 0.9853
6.750 0.8884 0.01261 0.00592 -0.0155 0.1945 0.9862
7.000 0.9170 0.01284 0.00616 -0.0160 0.1866 0.9871
7.250 0.9445 0.01314 0.00643 -0.0163 0.1773 0.9882
7.500 0.9716 0.01344 0.00672 -0.0165 0.1679 0.9894
7.750 0.9984 0.01374 0.00700 -0.0167 0.1587 0.9907
8.000 1.0240 0.01409 0.00732 -0.0167 0.1475 0.9922
8.250 1.0489 0.01447 0.00767 -0.0166 0.1342 0.9937
8.500 1.0740 0.01503 0.00810 -0.0168 0.1091 0.9947
8.750 1.0975 0.01579 0.00870 -0.0168 0.0880 0.9959
9.000 1.1234 0.01627 0.00919 -0.0171 0.0818 0.9972
9.250 1.1479 0.01686 0.00977 -0.0172 0.0747 0.9986
9.500 1.1734 0.01729 0.01023 -0.0173 0.0685 0.9998
9.750 1.1862 0.01781 0.01075 -0.0150 0.0606 1.0000
10.000 1.1841 0.01887 0.01158 -0.0102 0.0313 1.0000
10.250 1.1840 0.01968 0.01235 -0.0057 0.0221 1.0000
10.500 1.1822 0.02028 0.01296 -0.0007 0.0190 1.0000
10.750 1.1834 0.02085 0.01358 0.0036 0.0174 1.0000
11.000 1.1891 0.02160 0.01436 0.0066 0.0159 1.0000
11.250 1.1974 0.02246 0.01527 0.0089 0.0146 1.0000
11.500 1.2083 0.02330 0.01619 0.0107 0.0138 1.0000
11.750 1.2189 0.02427 0.01722 0.0122 0.0131 1.0000
12.000 1.2286 0.02538 0.01840 0.0136 0.0124 1.0000
12.250 1.2372 0.02666 0.01975 0.0149 0.0118 1.0000
12.500 1.2439 0.02817 0.02133 0.0161 0.0113 1.0000
12.750 1.2534 0.02952 0.02277 0.0170 0.0110 1.0000
13.000 1.2618 0.03101 0.02435 0.0178 0.0106 1.0000
13.250 1.2689 0.03266 0.02610 0.0185 0.0102 1.0000
13.500 1.2751 0.03446 0.02797 0.0191 0.0099 1.0000
13.750 1.2801 0.03641 0.03001 0.0196 0.0096 1.0000
14.000 1.2835 0.03857 0.03225 0.0200 0.0093 1.0000
14.250 1.2847 0.04103 0.03480 0.0203 0.0090 1.0000
14.500 1.2832 0.04383 0.03770 0.0205 0.0088 1.0000
14.750 1.2782 0.04713 0.04111 0.0204 0.0086 1.0000
15.000 1.2752 0.05034 0.04443 0.0201 0.0084 1.0000
15.250 1.2723 0.05368 0.04788 0.0196 0.0083 1.0000
15.500 1.2681 0.05735 0.05167 0.0188 0.0082 1.0000
15.750 1.2624 0.06140 0.05583 0.0177 0.0081 1.0000
16.000 1.2550 0.06580 0.06037 0.0164 0.0080 1.0000
16.250 1.2465 0.07054 0.06523 0.0149 0.0079 1.0000
16.500 1.2362 0.07568 0.07050 0.0130 0.0078 1.0000
16.750 1.2250 0.08104 0.07598 0.0110 0.0077 1.0000
17.000 1.2125 0.08670 0.08177 0.0089 0.0077 1.0000
17.250 1.2000 0.09245 0.08763 0.0066 0.0076 1.0000
17.500 1.1872 0.09831 0.09360 0.0043 0.0075 1.0000
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Polar data table (+)
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