GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 598 AIRFOIL (goe598-il) Reynolds number: 500,000 Max Cl/Cd: 54.61 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe598-il-500000-n5.txt Download as CSV file: xf-goe598-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6455 0.08721 0.08513 0.0054 1.0000 0.0035
-8.500 -0.6486 0.08176 0.07970 0.0015 1.0000 0.0035
-8.250 -0.6521 0.07575 0.07373 -0.0046 1.0000 0.0035
-8.000 -0.6500 0.06766 0.06560 -0.0141 1.0000 0.0034
-7.750 -0.6466 0.05936 0.05719 -0.0211 1.0000 0.0034
-7.500 -0.6420 0.05063 0.04825 -0.0259 1.0000 0.0034
-7.250 -0.6371 0.04063 0.03785 -0.0284 1.0000 0.0034
-7.000 -0.6362 0.02701 0.02327 -0.0283 1.0000 0.0035
-6.750 -0.6180 0.02257 0.01815 -0.0275 1.0000 0.0038
-6.500 -0.5981 0.01930 0.01438 -0.0269 1.0000 0.0042
-6.250 -0.5751 0.01741 0.01217 -0.0263 1.0000 0.0043
-6.000 -0.5512 0.01595 0.01047 -0.0258 1.0000 0.0046
-5.750 -0.5269 0.01472 0.00903 -0.0252 1.0000 0.0049
-5.500 -0.5024 0.01363 0.00776 -0.0247 1.0000 0.0053
-5.250 -0.4778 0.01270 0.00664 -0.0241 1.0000 0.0059
-5.000 -0.4530 0.01199 0.00580 -0.0235 1.0000 0.0063
-4.750 -0.4285 0.01130 0.00505 -0.0231 1.0000 0.0080
-4.500 -0.4036 0.01079 0.00447 -0.0225 1.0000 0.0094
-4.250 -0.3788 0.01023 0.00381 -0.0219 1.0000 0.0112
-4.000 -0.3537 0.00987 0.00344 -0.0214 1.0000 0.0170
-3.750 -0.3230 0.00957 0.00310 -0.0222 0.9975 0.0221
-3.500 -0.2897 0.00932 0.00280 -0.0236 0.9940 0.0282
-3.250 -0.2569 0.00906 0.00248 -0.0248 0.9893 0.0325
-3.000 -0.2243 0.00874 0.00210 -0.0260 0.9838 0.0379
-2.750 -0.1911 0.00853 0.00187 -0.0272 0.9777 0.0438
-2.500 -0.1595 0.00828 0.00172 -0.0282 0.9696 0.0687
-2.250 -0.1279 0.00818 0.00157 -0.0290 0.9606 0.0770
-2.000 -0.0972 0.00803 0.00144 -0.0297 0.9498 0.0858
-1.750 -0.0678 0.00790 0.00132 -0.0300 0.9361 0.0958
-1.500 -0.0398 0.00779 0.00121 -0.0300 0.9184 0.1039
-1.250 -0.0131 0.00763 0.00109 -0.0296 0.8958 0.1288
-1.000 0.0122 0.00731 0.00098 -0.0292 0.8694 0.2173
-0.500 0.0632 0.00668 0.00082 -0.0284 0.8213 0.4185
-0.250 0.0892 0.00643 0.00082 -0.0282 0.8024 0.5138
0.000 0.1153 0.00623 0.00082 -0.0279 0.7818 0.5942
0.250 0.1403 0.00600 0.00084 -0.0272 0.7546 0.6885
0.500 0.1615 0.00561 0.00090 -0.0255 0.7282 0.8317
0.750 0.1852 0.00546 0.00095 -0.0240 0.7069 0.9403
1.000 0.2241 0.00552 0.00097 -0.0264 0.6831 0.9878
1.250 0.2555 0.00567 0.00100 -0.0272 0.6507 1.0000
1.500 0.2820 0.00582 0.00104 -0.0270 0.6238 1.0000
1.750 0.3088 0.00595 0.00111 -0.0268 0.6005 1.0000
2.000 0.3353 0.00614 0.00120 -0.0265 0.5599 1.0000
2.250 0.3602 0.00661 0.00129 -0.0261 0.4517 1.0000
2.500 0.3836 0.00756 0.00158 -0.0258 0.2907 1.0000
2.750 0.4079 0.00839 0.00186 -0.0257 0.1541 1.0000
3.000 0.4331 0.00903 0.00216 -0.0255 0.0662 1.0000
3.250 0.4589 0.00956 0.00250 -0.0253 0.0218 1.0000
3.500 0.4855 0.00991 0.00287 -0.0251 0.0131 1.0000
3.750 0.5121 0.01029 0.00334 -0.0248 0.0104 1.0000
4.000 0.5374 0.01109 0.00426 -0.0243 0.0079 1.0000
4.250 0.5638 0.01147 0.00470 -0.0240 0.0070 1.0000
4.500 0.5892 0.01212 0.00544 -0.0236 0.0063 1.0000
4.750 0.6143 0.01287 0.00626 -0.0231 0.0057 1.0000
5.000 0.6390 0.01374 0.00723 -0.0226 0.0053 1.0000
5.250 0.6630 0.01485 0.00844 -0.0219 0.0050 1.0000
5.500 0.6859 0.01653 0.01028 -0.0211 0.0046 1.0000
5.750 0.7116 0.01725 0.01117 -0.0206 0.0040 1.0000
6.000 0.7356 0.01892 0.01308 -0.0198 0.0037 1.0000
6.250 0.7588 0.02091 0.01538 -0.0188 0.0034 1.0000
6.500 0.7811 0.02312 0.01791 -0.0178 0.0032 1.0000
6.750 0.8014 0.02587 0.02103 -0.0167 0.0031 1.0000
7.000 0.8183 0.02978 0.02545 -0.0151 0.0031 1.0000
7.250 0.8274 0.03707 0.03340 -0.0124 0.0032 1.0000
7.500 0.8341 0.04365 0.04045 -0.0105 0.0035 1.0000
7.750 0.8389 0.04974 0.04688 -0.0094 0.0037 1.0000
8.000 0.8409 0.05552 0.05293 -0.0090 0.0038 1.0000
8.250 0.8397 0.06111 0.05872 -0.0092 0.0040 1.0000
8.500 0.8347 0.06669 0.06447 -0.0103 0.0041 1.0000
8.750 0.8245 0.07219 0.07009 -0.0120 0.0042 1.0000
9.000 0.8109 0.07866 0.07664 -0.0169 0.0042 1.0000
9.250 0.8019 0.08759 0.08554 -0.0264 0.0042 1.0000
9.500 0.7962 0.09431 0.09224 -0.0314 0.0043 1.0000
9.750 0.7916 0.10021 0.09812 -0.0350 0.0044 1.0000
10.000 0.7868 0.10573 0.10362 -0.0380 0.0045 1.0000
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Polar data table (+)
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