GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 392 AIRFOIL (goe392-il) Reynolds number: 100,000 Max Cl/Cd: 58.08 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe392-il-100000-n5.txt Download as CSV file: xf-goe392-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 392 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3096 0.10779 0.10346 -0.0415 1.0000 0.0316
-8.250 -0.3169 0.10598 0.10175 -0.0405 1.0000 0.0317
-8.000 -0.3268 0.10451 0.10038 -0.0388 1.0000 0.0317
-7.750 -0.3160 0.10068 0.09659 -0.0441 0.9942 0.0319
-7.500 -0.2998 0.09616 0.09208 -0.0511 0.9855 0.0319
-7.250 -0.2844 0.09050 0.08645 -0.0539 0.9797 0.0324
-7.000 -0.2688 0.08624 0.08217 -0.0550 0.9732 0.0334
-6.750 -0.2506 0.08178 0.07770 -0.0597 0.9643 0.0342
-6.500 -0.2293 0.07710 0.07297 -0.0659 0.9562 0.0357
-6.000 -0.1876 0.06737 0.06315 -0.0808 0.9337 0.0398
-5.750 -0.1508 0.06101 0.05631 -0.0959 0.9212 0.0419
-5.500 -0.1407 0.05706 0.05267 -0.0933 0.9173 0.0459
-5.250 -0.1079 0.05206 0.04714 -0.1026 0.9063 0.0541
-5.000 -0.0842 0.04706 0.04218 -0.1054 0.9020 0.0580
-4.500 -0.0148 0.03587 0.02973 -0.1112 0.8873 0.0208
-4.250 0.0114 0.03238 0.02580 -0.1124 0.8787 0.0203
-4.000 0.0447 0.02916 0.02203 -0.1142 0.8732 0.0200
-3.750 0.0741 0.02666 0.01900 -0.1147 0.8652 0.0201
-3.250 0.1381 0.02248 0.01388 -0.1162 0.8515 0.0240
-3.000 0.1716 0.02077 0.01188 -0.1170 0.8454 0.0256
-2.750 0.2015 0.01947 0.01039 -0.1170 0.8375 0.0281
-2.500 0.2317 0.01834 0.00909 -0.1173 0.8300 0.0342
-2.250 0.2620 0.01745 0.00799 -0.1177 0.8222 0.0409
-2.000 0.2906 0.01666 0.00699 -0.1178 0.8136 0.0547
-1.750 0.3207 0.01508 0.00635 -0.1188 0.8065 0.2946
-1.500 0.3466 0.01471 0.00618 -0.1184 0.7969 0.4482
-1.250 0.3735 0.01411 0.00599 -0.1181 0.7889 0.5768
-1.000 0.3986 0.01346 0.00586 -0.1167 0.7801 0.7848
-0.750 0.4509 0.01322 0.00546 -0.1217 0.7715 1.0000
-0.500 0.4807 0.01328 0.00524 -0.1221 0.7628 1.0000
-0.250 0.5066 0.01340 0.00515 -0.1218 0.7521 1.0000
0.000 0.5328 0.01351 0.00507 -0.1215 0.7417 1.0000
0.250 0.5599 0.01361 0.00498 -0.1214 0.7316 1.0000
0.500 0.5871 0.01371 0.00491 -0.1213 0.7214 1.0000
0.750 0.6120 0.01384 0.00494 -0.1208 0.7100 1.0000
1.000 0.6374 0.01397 0.00496 -0.1204 0.6993 1.0000
1.250 0.6638 0.01410 0.00499 -0.1201 0.6895 1.0000
1.500 0.6897 0.01424 0.00505 -0.1198 0.6797 1.0000
1.750 0.7145 0.01441 0.00520 -0.1193 0.6693 1.0000
2.000 0.7402 0.01457 0.00531 -0.1189 0.6598 1.0000
2.250 0.7663 0.01472 0.00543 -0.1187 0.6506 1.0000
2.500 0.7907 0.01492 0.00568 -0.1181 0.6403 1.0000
2.750 0.8160 0.01511 0.00589 -0.1177 0.6309 1.0000
3.000 0.8419 0.01530 0.00609 -0.1174 0.6220 1.0000
3.250 0.8660 0.01552 0.00640 -0.1168 0.6119 1.0000
3.500 0.8911 0.01575 0.00674 -0.1163 0.6025 1.0000
3.750 0.9154 0.01595 0.00701 -0.1156 0.5905 1.0000
4.000 0.9299 0.01601 0.00690 -0.1125 0.5476 1.0000
4.250 0.9418 0.01633 0.00696 -0.1091 0.4928 1.0000
4.500 0.9494 0.01703 0.00721 -0.1052 0.4071 1.0000
5.000 0.9364 0.02179 0.00975 -0.0946 0.0337 1.0000
5.250 0.9518 0.02270 0.01079 -0.0924 0.0252 1.0000
5.500 0.9658 0.02367 0.01198 -0.0901 0.0227 1.0000
5.750 0.9794 0.02455 0.01311 -0.0877 0.0215 1.0000
6.000 0.9898 0.02555 0.01433 -0.0848 0.0195 1.0000
6.250 0.9958 0.02679 0.01576 -0.0815 0.0176 1.0000
6.500 0.9984 0.02821 0.01736 -0.0779 0.0169 1.0000
6.750 0.9968 0.02988 0.01927 -0.0740 0.0165 1.0000
7.000 0.9940 0.03171 0.02122 -0.0703 0.0162 1.0000
7.250 0.9922 0.03366 0.02323 -0.0669 0.0160 1.0000
7.500 0.9971 0.03565 0.02518 -0.0642 0.0158 1.0000
7.750 1.0172 0.03715 0.02664 -0.0628 0.0155 1.0000
8.000 1.0383 0.03841 0.02804 -0.0617 0.0148 1.0000
8.250 1.0658 0.03988 0.02966 -0.0610 0.0139 1.0000
8.500 1.1184 0.04241 0.03228 -0.0630 0.0140 1.0000
8.750 1.1783 0.04647 0.03653 -0.0671 0.0147 1.0000
9.000 1.2240 0.05014 0.04050 -0.0693 0.0167 1.0000
9.250 1.2379 0.05206 0.04300 -0.0659 0.0199 1.0000
17.250 1.0197 0.21783 0.21321 -0.1045 0.0363 1.0000
18.750 0.8055 0.22400 0.22022 -0.1002 0.0375 1.0000
19.000 0.8062 0.22794 0.22417 -0.1024 0.0346 1.0000
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Polar data table (+)
Polar graphs
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