GOE 391 AIRFOIL (goe391-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 391 AIRFOIL (goe391-il) Reynolds number: 50,000 Max Cl/Cd: 39.62 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe391-il-50000.txt Download as CSV file: xf-goe391-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 391 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4482 0.10238 0.09546 -0.0187 1.0000 0.1294
-7.750 -0.4601 0.10166 0.09489 -0.0208 1.0000 0.1316
-7.500 -0.4482 0.09645 0.08972 -0.0181 1.0000 0.1381
-7.250 -0.4512 0.09444 0.08779 -0.0198 1.0000 0.1440
-7.000 -0.4527 0.09182 0.08526 -0.0218 1.0000 0.1474
-6.750 -0.4461 0.08826 0.08174 -0.0202 1.0000 0.1571
-6.500 -0.4438 0.08500 0.07856 -0.0206 1.0000 0.1635
-6.250 -0.4430 0.08333 0.07689 -0.0239 1.0000 0.1735
-6.000 -0.4358 0.07909 0.07273 -0.0207 1.0000 0.1846
-5.750 -0.4311 0.07587 0.06956 -0.0201 1.0000 0.1967
-5.500 -0.4262 0.07295 0.06667 -0.0200 1.0000 0.2120
-5.250 -0.4216 0.07024 0.06392 -0.0212 1.0000 0.2307
-5.000 -0.0732 0.04279 0.03551 -0.0247 1.0000 1.0000
-4.750 -0.0638 0.04081 0.03357 -0.0252 1.0000 1.0000
-4.500 -0.0546 0.03888 0.03169 -0.0256 1.0000 1.0000
-4.250 -0.0455 0.03706 0.02993 -0.0260 1.0000 1.0000
-4.000 -0.0872 0.03836 0.03147 -0.0138 1.0000 0.9734
-3.750 -0.1339 0.03965 0.03301 -0.0015 1.0000 0.9413
-3.500 -0.1743 0.03989 0.03349 0.0082 1.0000 0.9040
-3.250 -0.2200 0.04014 0.03400 0.0182 1.0000 0.8733
-3.000 -0.2717 0.04030 0.03444 0.0288 1.0000 0.8442
-2.750 -0.3281 0.04015 0.03456 0.0393 1.0000 0.8100
-2.250 -0.1816 0.03343 0.02509 -0.0320 1.0000 0.2676
-2.000 -0.1381 0.03122 0.02190 -0.0339 1.0000 0.1986
-1.750 -0.1057 0.02920 0.01924 -0.0336 1.0000 0.1697
-1.500 -0.0766 0.02751 0.01704 -0.0329 1.0000 0.1556
-1.250 -0.0495 0.02603 0.01520 -0.0322 1.0000 0.1546
-1.000 -0.0221 0.02481 0.01358 -0.0316 1.0000 0.1563
-0.750 0.0042 0.02369 0.01219 -0.0306 1.0000 0.1548
-0.500 0.0332 0.02279 0.01099 -0.0300 1.0000 0.1566
-0.250 0.0612 0.02198 0.01002 -0.0296 1.0000 0.1637
0.000 0.0862 0.02131 0.00935 -0.0289 1.0000 0.1799
0.250 0.1105 0.02075 0.00878 -0.0281 1.0000 0.1949
0.750 0.1698 0.01796 0.00777 -0.0282 1.0000 1.0000
1.000 0.1907 0.01828 0.00764 -0.0271 1.0000 1.0000
1.250 0.2107 0.01863 0.00776 -0.0261 1.0000 1.0000
1.500 0.2304 0.01902 0.00799 -0.0253 1.0000 1.0000
1.750 0.2496 0.01945 0.00831 -0.0245 1.0000 1.0000
2.000 0.2684 0.01993 0.00872 -0.0237 1.0000 1.0000
2.250 0.2868 0.02047 0.00922 -0.0230 1.0000 1.0000
2.500 0.3046 0.02106 0.00980 -0.0223 1.0000 1.0000
2.750 0.3219 0.02172 0.01047 -0.0218 1.0000 1.0000
3.000 0.3387 0.02244 0.01124 -0.0212 1.0000 1.0000
3.250 0.3549 0.02325 0.01213 -0.0208 1.0000 1.0000
3.500 0.3706 0.02414 0.01310 -0.0204 1.0000 1.0000
3.750 0.3986 0.02536 0.01445 -0.0228 0.9940 1.0000
4.000 0.4662 0.02699 0.01639 -0.0324 0.9649 1.0000
4.250 0.5459 0.02796 0.01789 -0.0426 0.9262 1.0000
4.500 0.6297 0.02754 0.01809 -0.0512 0.8781 1.0000
4.750 0.7417 0.02316 0.01480 -0.0572 0.8018 1.0000
5.000 0.7888 0.01991 0.01186 -0.0519 0.6806 1.0000
5.250 0.7939 0.02153 0.01123 -0.0428 0.3287 1.0000
5.500 0.8041 0.02504 0.01331 -0.0397 0.1905 1.0000
5.750 0.8358 0.02752 0.01551 -0.0395 0.1598 1.0000
6.000 0.8709 0.03010 0.01814 -0.0398 0.1422 1.0000
6.250 0.8995 0.03248 0.02070 -0.0392 0.1277 1.0000
6.500 0.9283 0.03536 0.02396 -0.0384 0.1214 1.0000
6.750 0.9514 0.03843 0.02738 -0.0372 0.1143 1.0000
7.000 0.9711 0.04143 0.03087 -0.0355 0.1084 1.0000
7.250 0.9885 0.04534 0.03539 -0.0334 0.1085 1.0000
7.500 1.0005 0.04975 0.04046 -0.0311 0.1106 1.0000
7.750 1.0089 0.05434 0.04567 -0.0288 0.1130 1.0000
8.000 1.0146 0.05893 0.05070 -0.0268 0.1143 1.0000
8.250 1.0179 0.06367 0.05581 -0.0250 0.1153 1.0000
8.500 1.0161 0.06861 0.06118 -0.0232 0.1192 1.0000
8.750 1.0018 0.07478 0.06774 -0.0222 0.1281 1.0000
9.000 0.9674 0.08247 0.07576 -0.0234 0.1503 1.0000
9.250 0.8511 0.07972 0.07339 -0.0167 0.1482 1.0000
9.500 0.8163 0.08733 0.08097 -0.0205 0.1532 1.0000
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Polar data table (+)
Polar graphs
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