GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 598 AIRFOIL (goe598-il) Reynolds number: 100,000 Max Cl/Cd: 40.4 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe598-il-100000-n5.txt Download as CSV file: xf-goe598-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4928 0.09793 0.09330 -0.0024 1.0000 0.0260
-9.250 -0.4953 0.09335 0.08875 -0.0037 1.0000 0.0252
-9.000 -0.6149 0.09894 0.09419 0.0029 1.0000 0.0193
-8.750 -0.6143 0.09422 0.08952 0.0004 1.0000 0.0192
-8.500 -0.6142 0.08936 0.08469 -0.0026 1.0000 0.0191
-8.250 -0.6147 0.08432 0.07971 -0.0062 1.0000 0.0190
-8.000 -0.6145 0.07870 0.07411 -0.0115 1.0000 0.0189
-7.750 -0.6113 0.07267 0.06805 -0.0167 1.0000 0.0187
-7.500 -0.6070 0.06674 0.06203 -0.0208 1.0000 0.0187
-7.250 -0.6009 0.06087 0.05600 -0.0241 1.0000 0.0187
-7.000 -0.5929 0.05517 0.05006 -0.0264 1.0000 0.0187
-6.750 -0.5827 0.04969 0.04426 -0.0280 1.0000 0.0187
-6.500 -0.5702 0.04449 0.03867 -0.0289 1.0000 0.0186
-6.250 -0.5551 0.03962 0.03331 -0.0292 1.0000 0.0186
-6.000 -0.5372 0.03522 0.02831 -0.0290 1.0000 0.0188
-5.750 -0.5166 0.03144 0.02383 -0.0284 1.0000 0.0191
-5.500 -0.4945 0.02818 0.01997 -0.0278 1.0000 0.0198
-5.250 -0.4731 0.02558 0.01714 -0.0275 1.0000 0.0227
-5.000 -0.4488 0.02339 0.01456 -0.0268 1.0000 0.0251
-4.750 -0.4238 0.02129 0.01209 -0.0259 1.0000 0.0274
-4.500 -0.3998 0.01958 0.01019 -0.0251 1.0000 0.0323
-4.250 -0.3761 0.01812 0.00860 -0.0243 1.0000 0.0375
-4.000 -0.3525 0.01698 0.00740 -0.0236 1.0000 0.0472
-3.750 -0.3281 0.01622 0.00661 -0.0230 1.0000 0.0610
-3.500 -0.3036 0.01543 0.00578 -0.0223 1.0000 0.0789
-3.250 -0.2794 0.01467 0.00500 -0.0217 1.0000 0.1065
-3.000 -0.2556 0.01390 0.00444 -0.0213 1.0000 0.1597
-2.750 -0.2316 0.01319 0.00401 -0.0210 1.0000 0.2431
-2.500 -0.2091 0.01216 0.00373 -0.0205 1.0000 0.4207
-2.250 -0.1864 0.01162 0.00357 -0.0194 1.0000 0.5500
-2.000 -0.1634 0.01126 0.00339 -0.0183 1.0000 0.6366
-1.750 -0.1433 0.01082 0.00336 -0.0160 1.0000 0.7572
-1.500 -0.1086 0.01052 0.00335 -0.0161 1.0000 0.9259
-1.250 -0.0663 0.01046 0.00313 -0.0194 1.0000 1.0000
-1.000 -0.0454 0.01049 0.00304 -0.0184 1.0000 1.0000
-0.750 -0.0241 0.01055 0.00300 -0.0176 1.0000 1.0000
-0.500 -0.0027 0.01064 0.00301 -0.0168 1.0000 1.0000
-0.250 0.0312 0.01075 0.00303 -0.0186 0.9936 1.0000
0.000 0.0708 0.01084 0.00306 -0.0215 0.9838 1.0000
0.250 0.1103 0.01093 0.00313 -0.0243 0.9739 1.0000
0.500 0.1492 0.01101 0.00321 -0.0270 0.9636 1.0000
0.750 0.1871 0.01108 0.00331 -0.0293 0.9528 1.0000
1.000 0.2238 0.01114 0.00342 -0.0313 0.9391 1.0000
1.250 0.2582 0.01117 0.00354 -0.0326 0.9212 1.0000
1.500 0.2920 0.01119 0.00363 -0.0336 0.9015 1.0000
1.750 0.3236 0.01120 0.00371 -0.0339 0.8783 1.0000
2.000 0.3529 0.01121 0.00381 -0.0336 0.8519 1.0000
2.250 0.3801 0.01127 0.00393 -0.0328 0.8251 1.0000
2.500 0.4062 0.01137 0.00409 -0.0319 0.7973 1.0000
2.750 0.4316 0.01150 0.00434 -0.0308 0.7678 1.0000
3.000 0.4562 0.01166 0.00456 -0.0295 0.7312 1.0000
3.250 0.4792 0.01186 0.00475 -0.0277 0.6736 1.0000
3.500 0.4929 0.01290 0.00461 -0.0238 0.4074 1.0000
3.750 0.5068 0.01544 0.00545 -0.0224 0.0956 1.0000
4.000 0.5283 0.01704 0.00672 -0.0214 0.0381 1.0000
4.250 0.5521 0.01810 0.00792 -0.0205 0.0300 1.0000
4.500 0.5753 0.01926 0.00919 -0.0196 0.0260 1.0000
4.750 0.5982 0.02060 0.01066 -0.0187 0.0224 1.0000
5.000 0.6216 0.02218 0.01239 -0.0176 0.0207 1.0000
5.250 0.6460 0.02407 0.01451 -0.0166 0.0197 1.0000
5.500 0.6711 0.02624 0.01694 -0.0156 0.0190 1.0000
5.750 0.6950 0.02838 0.01938 -0.0148 0.0175 1.0000
6.000 0.7161 0.03122 0.02253 -0.0141 0.0159 1.0000
6.250 0.7354 0.03508 0.02689 -0.0130 0.0154 1.0000
6.500 0.7539 0.03852 0.03083 -0.0119 0.0154 1.0000
6.750 0.7708 0.04193 0.03470 -0.0108 0.0155 1.0000
7.000 0.7863 0.04533 0.03856 -0.0097 0.0157 1.0000
7.250 0.8000 0.04897 0.04267 -0.0085 0.0161 1.0000
7.500 0.8087 0.05400 0.04827 -0.0074 0.0171 1.0000
7.750 0.8110 0.06005 0.05477 -0.0070 0.0182 1.0000
8.000 0.8099 0.06576 0.06077 -0.0073 0.0191 1.0000
8.250 0.8056 0.07124 0.06646 -0.0084 0.0198 1.0000
8.500 0.7978 0.07664 0.07199 -0.0102 0.0203 1.0000
8.750 0.7869 0.08217 0.07759 -0.0133 0.0207 1.0000
9.000 0.7785 0.08903 0.08447 -0.0194 0.0211 1.0000
9.250 0.7736 0.09576 0.09116 -0.0248 0.0216 1.0000
9.500 0.7703 0.10159 0.09695 -0.0284 0.0223 1.0000
9.750 0.7683 0.10677 0.10210 -0.0308 0.0231 1.0000
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