GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 598 AIRFOIL (goe598-il) Reynolds number: 200,000 Max Cl/Cd: 48.59 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe598-il-200000-n5.txt Download as CSV file: xf-goe598-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 598 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6205 0.08191 0.07865 -0.0028 1.0000 0.0101
-8.000 -0.6228 0.07596 0.07274 -0.0087 1.0000 0.0099
-7.750 -0.6202 0.06905 0.06579 -0.0157 1.0000 0.0098
-7.500 -0.6160 0.06229 0.05893 -0.0209 1.0000 0.0096
-7.250 -0.6097 0.05564 0.05210 -0.0247 1.0000 0.0094
-7.000 -0.6012 0.04909 0.04530 -0.0272 1.0000 0.0092
-6.750 -0.5903 0.04268 0.03854 -0.0286 1.0000 0.0091
-6.500 -0.5770 0.03659 0.03198 -0.0290 1.0000 0.0090
-6.250 -0.5607 0.03139 0.02621 -0.0288 1.0000 0.0090
-6.000 -0.5413 0.02719 0.02140 -0.0281 1.0000 0.0092
-5.750 -0.5192 0.02421 0.01788 -0.0274 1.0000 0.0098
-5.500 -0.4966 0.02144 0.01453 -0.0267 1.0000 0.0111
-5.250 -0.4732 0.01926 0.01204 -0.0260 1.0000 0.0122
-5.000 -0.4489 0.01770 0.01024 -0.0253 1.0000 0.0133
-4.750 -0.4244 0.01638 0.00874 -0.0246 1.0000 0.0150
-4.500 -0.3994 0.01557 0.00775 -0.0240 1.0000 0.0185
-4.250 -0.3756 0.01432 0.00640 -0.0232 1.0000 0.0214
-4.000 -0.3511 0.01361 0.00557 -0.0227 1.0000 0.0281
-3.750 -0.3269 0.01277 0.00463 -0.0221 1.0000 0.0344
-3.500 -0.3024 0.01214 0.00396 -0.0216 1.0000 0.0439
-3.250 -0.2776 0.01168 0.00359 -0.0212 1.0000 0.0611
-3.000 -0.2525 0.01139 0.00326 -0.0207 1.0000 0.0834
-2.750 -0.2275 0.01112 0.00294 -0.0203 1.0000 0.0989
-2.500 -0.2027 0.01083 0.00270 -0.0199 1.0000 0.1201
-2.250 -0.1780 0.01042 0.00250 -0.0196 1.0000 0.1733
-2.000 -0.1500 0.00992 0.00230 -0.0202 0.9981 0.2646
-1.750 -0.1154 0.00933 0.00215 -0.0222 0.9921 0.3859
-1.500 -0.0809 0.00883 0.00209 -0.0240 0.9858 0.5164
-1.250 -0.0476 0.00847 0.00202 -0.0253 0.9778 0.6072
-1.000 -0.0170 0.00809 0.00201 -0.0258 0.9684 0.7026
-0.750 0.0102 0.00770 0.00208 -0.0250 0.9583 0.8317
-0.500 0.0550 0.00755 0.00211 -0.0279 0.9535 0.9626
-0.250 0.0985 0.00751 0.00203 -0.0314 0.9431 1.0000
0.000 0.1316 0.00750 0.00198 -0.0325 0.9271 1.0000
0.250 0.1621 0.00749 0.00193 -0.0330 0.9062 1.0000
0.750 0.2184 0.00752 0.00186 -0.0326 0.8617 1.0000
1.000 0.2441 0.00758 0.00186 -0.0319 0.8358 1.0000
1.250 0.2690 0.00768 0.00187 -0.0309 0.8066 1.0000
1.500 0.2940 0.00781 0.00191 -0.0301 0.7781 1.0000
1.750 0.3197 0.00794 0.00199 -0.0294 0.7540 1.0000
2.000 0.3456 0.00807 0.00212 -0.0289 0.7318 1.0000
2.250 0.3710 0.00823 0.00223 -0.0282 0.7010 1.0000
2.500 0.3959 0.00844 0.00235 -0.0273 0.6603 1.0000
2.750 0.4213 0.00867 0.00254 -0.0267 0.6204 1.0000
3.000 0.4431 0.00926 0.00263 -0.0253 0.4777 1.0000
3.250 0.4601 0.01105 0.00309 -0.0242 0.1982 1.0000
3.500 0.4819 0.01238 0.00370 -0.0238 0.0513 1.0000
3.750 0.5067 0.01321 0.00444 -0.0233 0.0233 1.0000
4.000 0.5320 0.01390 0.00525 -0.0228 0.0171 1.0000
4.250 0.5562 0.01491 0.00642 -0.0220 0.0149 1.0000
4.500 0.5802 0.01594 0.00759 -0.0213 0.0139 1.0000
4.750 0.6043 0.01705 0.00880 -0.0205 0.0123 1.0000
5.000 0.6286 0.01816 0.01002 -0.0198 0.0106 1.0000
5.250 0.6527 0.01969 0.01175 -0.0190 0.0100 1.0000
5.500 0.6771 0.02148 0.01375 -0.0181 0.0096 1.0000
5.750 0.7011 0.02359 0.01616 -0.0172 0.0094 1.0000
6.000 0.7244 0.02607 0.01902 -0.0161 0.0093 1.0000
6.250 0.7462 0.02903 0.02243 -0.0149 0.0093 1.0000
6.500 0.7654 0.03190 0.02569 -0.0139 0.0089 1.0000
6.750 0.7779 0.03642 0.03069 -0.0127 0.0082 1.0000
7.000 0.7909 0.04057 0.03538 -0.0113 0.0076 1.0000
7.250 0.8022 0.04479 0.04001 -0.0102 0.0075 1.0000
7.500 0.8082 0.04963 0.04521 -0.0093 0.0077 1.0000
8.000 0.8155 0.05839 0.05453 -0.0083 0.0081 1.0000
8.250 0.8212 0.06218 0.05854 -0.0081 0.0084 1.0000
8.500 0.8138 0.07179 0.06843 -0.0101 0.0100 1.0000
8.750 0.8001 0.07809 0.07484 -0.0132 0.0103 1.0000
9.000 0.7894 0.08593 0.08272 -0.0209 0.0105 1.0000
9.250 0.7827 0.09357 0.09032 -0.0273 0.0109 1.0000
9.500 0.7776 0.10004 0.09675 -0.0315 0.0114 1.0000
9.750 0.7737 0.10595 0.10263 -0.0348 0.0121 1.0000
10.000 0.7710 0.11139 0.10804 -0.0374 0.0129 1.0000
10.500 0.6262 0.10869 0.10548 -0.0242 0.0111 1.0000
10.750 0.6209 0.11371 0.11048 -0.0257 0.0116 1.0000
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Polar data table (+)
Polar graphs
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