GOE 491 AIRFOIL (goe491-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 491 AIRFOIL (goe491-il) Reynolds number: 500,000 Max Cl/Cd: 92.25 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe491-il-500000.txt Download as CSV file: xf-goe491-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 491 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4841 0.09101 0.08874 -0.0029 1.0000 0.0144
-7.750 -0.4843 0.08782 0.08558 -0.0044 1.0000 0.0154
-7.500 -0.4854 0.08486 0.08265 -0.0056 1.0000 0.0155
-7.250 -0.4779 0.08124 0.07903 -0.0111 1.0000 0.0162
-7.000 -0.4688 0.07767 0.07546 -0.0136 1.0000 0.0164
-6.750 -0.4580 0.07378 0.07154 -0.0163 1.0000 0.0165
-6.500 -0.4469 0.06994 0.06766 -0.0182 1.0000 0.0165
-6.250 -0.4489 0.06421 0.06194 -0.0187 1.0000 0.0174
-6.000 -0.4379 0.06220 0.05991 -0.0181 1.0000 0.0183
-5.750 -0.4246 0.05911 0.05677 -0.0189 1.0000 0.0191
-5.500 -0.4099 0.05577 0.05338 -0.0198 1.0000 0.0200
-5.250 -0.3938 0.05228 0.04981 -0.0206 1.0000 0.0211
-5.000 -0.3670 0.04881 0.04617 -0.0220 1.0000 0.0234
-4.750 -0.3476 0.04563 0.04286 -0.0217 1.0000 0.0237
-3.250 -0.2525 0.01271 0.00716 -0.0116 0.9969 0.0176
-3.000 -0.2163 0.01166 0.00594 -0.0133 0.9941 0.0194
-2.750 -0.1813 0.01078 0.00489 -0.0145 0.9903 0.0215
-2.500 -0.1457 0.01015 0.00415 -0.0160 0.9865 0.0237
-2.250 -0.1089 0.00958 0.00358 -0.0178 0.9834 0.0307
-2.000 -0.0757 0.00945 0.00348 -0.0188 0.9769 0.0426
-1.750 -0.0379 0.00940 0.00343 -0.0208 0.9719 0.0527
-1.500 -0.0048 0.00935 0.00334 -0.0218 0.9637 0.0581
-1.250 0.0308 0.00895 0.00297 -0.0234 0.9572 0.0642
-1.000 0.0649 0.00883 0.00284 -0.0246 0.9465 0.0696
-0.750 0.1031 0.00835 0.00235 -0.0268 0.9361 0.0741
-0.500 0.1447 0.00801 0.00202 -0.0297 0.9227 0.0781
-0.250 0.1851 0.00779 0.00176 -0.0323 0.9039 0.0820
0.000 0.2171 0.00766 0.00154 -0.0329 0.8780 0.0860
0.250 0.2438 0.00755 0.00138 -0.0324 0.8442 0.0944
0.500 0.2678 0.00753 0.00125 -0.0312 0.7959 0.1065
0.750 0.2890 0.00750 0.00116 -0.0296 0.7352 0.1575
1.000 0.4027 0.00613 0.00145 -0.0492 0.6192 1.0000
1.250 0.4228 0.00647 0.00143 -0.0475 0.5437 1.0000
1.500 0.4446 0.00675 0.00145 -0.0462 0.4914 1.0000
1.750 0.4676 0.00696 0.00150 -0.0452 0.4617 1.0000
2.250 0.5147 0.00730 0.00162 -0.0433 0.4182 1.0000
2.500 0.5387 0.00745 0.00170 -0.0425 0.4015 1.0000
2.750 0.5628 0.00759 0.00178 -0.0416 0.3846 1.0000
3.000 0.5867 0.00774 0.00188 -0.0408 0.3663 1.0000
3.250 0.6109 0.00787 0.00197 -0.0400 0.3443 1.0000
3.500 0.6346 0.00807 0.00206 -0.0391 0.3139 1.0000
3.750 0.6573 0.00837 0.00218 -0.0381 0.2684 1.0000
4.000 0.6779 0.00896 0.00244 -0.0369 0.1923 1.0000
4.250 0.6979 0.00967 0.00280 -0.0355 0.1184 1.0000
4.500 0.7175 0.01048 0.00325 -0.0340 0.0521 1.0000
4.750 0.7405 0.01083 0.00360 -0.0330 0.0461 1.0000
5.000 0.7636 0.01119 0.00400 -0.0319 0.0428 1.0000
5.250 0.7865 0.01154 0.00445 -0.0309 0.0409 1.0000
5.500 0.8088 0.01198 0.00497 -0.0298 0.0385 1.0000
5.750 0.8298 0.01258 0.00562 -0.0285 0.0349 1.0000
6.000 0.8470 0.01371 0.00688 -0.0264 0.0314 1.0000
6.250 0.8701 0.01401 0.00724 -0.0255 0.0297 1.0000
6.500 0.8914 0.01457 0.00789 -0.0242 0.0267 1.0000
6.750 0.9112 0.01531 0.00867 -0.0228 0.0239 1.0000
7.000 0.9228 0.01753 0.01101 -0.0200 0.0211 1.0000
7.250 0.9467 0.01761 0.01117 -0.0192 0.0196 1.0000
7.500 0.9687 0.01802 0.01165 -0.0181 0.0176 1.0000
7.750 0.9891 0.01869 0.01238 -0.0169 0.0161 1.0000
8.000 1.0072 0.01974 0.01351 -0.0154 0.0150 1.0000
8.250 0.9788 0.01061 0.00489 -0.0087 0.0140 1.0000
8.500 0.9969 0.01159 0.00606 -0.0072 0.0134 1.0000
8.750 1.0122 0.01332 0.00800 -0.0053 0.0128 1.0000
9.000 1.0271 0.01483 0.00971 -0.0036 0.0119 1.0000
9.250 1.0417 0.01607 0.01111 -0.0019 0.0112 1.0000
9.500 1.0540 0.01756 0.01277 -0.0001 0.0107 1.0000
9.750 1.0636 0.01939 0.01477 0.0019 0.0103 1.0000
10.000 1.0687 0.02173 0.01735 0.0043 0.0100 1.0000
10.250 1.0670 0.02489 0.02078 0.0072 0.0099 1.0000
10.500 1.0578 0.02839 0.02454 0.0106 0.0097 1.0000
10.750 1.0399 0.03141 0.02778 0.0149 0.0097 1.0000
11.000 1.0192 0.03457 0.03114 0.0180 0.0096 1.0000
11.250 1.0003 0.03794 0.03470 0.0193 0.0097 1.0000
11.500 0.9802 0.04217 0.03910 0.0191 0.0097 1.0000
11.750 0.9569 0.04798 0.04511 0.0171 0.0099 1.0000
12.000 0.9306 0.05555 0.05286 0.0134 0.0100 1.0000
12.250 0.8566 0.07514 0.07280 0.0028 0.0111 1.0000
12.500 0.8176 0.08840 0.08619 -0.0044 0.0117 1.0000
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Polar data table (+)
Polar graphs
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