GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.06 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe330-il-1000000.txt Download as CSV file: xf-goe330-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 330 (PFALZ 59) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.1656 0.08651 0.08481 -0.0695 0.9413 0.0168
-8.500 -0.1615 0.08313 0.08138 -0.0711 0.9247 0.0168
-8.250 -0.1581 0.07953 0.07773 -0.0713 0.9113 0.0171
-8.000 -0.1481 0.07754 0.07570 -0.0717 0.8990 0.0173
-7.750 -0.1384 0.07529 0.07341 -0.0730 0.8873 0.0176
-7.500 -0.1283 0.07281 0.07088 -0.0752 0.8769 0.0180
-7.250 -0.1147 0.06988 0.06790 -0.0786 0.8680 0.0186
-6.500 -0.0530 0.05163 0.04941 -0.1047 0.8459 0.0211
-6.250 -0.0340 0.04963 0.04736 -0.1062 0.8396 0.0214
-6.000 -0.0129 0.04756 0.04523 -0.1081 0.8337 0.0217
-5.750 0.0103 0.04510 0.04271 -0.1106 0.8275 0.0222
-5.500 0.0352 0.04218 0.03967 -0.1137 0.8217 0.0233
-5.250 0.0731 0.03571 0.03291 -0.1198 0.8161 0.0255
-5.000 0.0922 0.02911 0.02601 -0.1228 0.8100 0.0262
-4.750 0.1159 0.02780 0.02461 -0.1232 0.8038 0.0266
-4.500 0.1405 0.02646 0.02318 -0.1237 0.7970 0.0272
-4.250 0.1653 0.02495 0.02152 -0.1240 0.7900 0.0281
-4.000 0.1957 0.02339 0.01971 -0.1238 0.7828 0.0313
-3.000 0.2925 0.01347 0.00858 -0.1229 0.7480 0.0308
-2.750 0.3182 0.01202 0.00687 -0.1224 0.7366 0.0307
-2.500 0.3443 0.01112 0.00576 -0.1220 0.7222 0.0307
-2.250 0.3703 0.01050 0.00497 -0.1216 0.7041 0.0308
-1.750 0.4218 0.00970 0.00385 -0.1206 0.6672 0.0310
-1.500 0.4479 0.00942 0.00345 -0.1202 0.6532 0.0311
-1.250 0.4746 0.00929 0.00324 -0.1198 0.6410 0.0314
-1.000 0.5003 0.00874 0.00259 -0.1194 0.6296 0.0322
-0.750 0.5264 0.00848 0.00225 -0.1190 0.6185 0.0330
-0.500 0.5526 0.00837 0.00207 -0.1187 0.6073 0.0338
-0.250 0.5797 0.00828 0.00195 -0.1185 0.5967 0.0346
0.000 0.6066 0.00823 0.00185 -0.1183 0.5857 0.0354
0.250 0.6334 0.00820 0.00177 -0.1180 0.5739 0.0363
0.500 0.6601 0.00820 0.00171 -0.1178 0.5606 0.0373
0.750 0.6868 0.00822 0.00166 -0.1175 0.5436 0.0385
1.000 0.7128 0.00826 0.00162 -0.1171 0.5190 0.0424
1.250 0.7377 0.00841 0.00168 -0.1166 0.4875 0.0526
1.500 0.7624 0.00860 0.00178 -0.1160 0.4595 0.0736
1.750 0.7877 0.00878 0.00187 -0.1156 0.4407 0.0820
2.000 0.8136 0.00889 0.00195 -0.1153 0.4278 0.0919
2.250 0.8398 0.00894 0.00205 -0.1151 0.4180 0.1303
2.500 0.8617 0.00807 0.00234 -0.1146 0.4095 0.6686
3.250 0.9515 0.00788 0.00271 -0.1161 0.3875 1.0000
3.500 0.9767 0.00804 0.00282 -0.1157 0.3807 1.0000
3.750 1.0021 0.00818 0.00293 -0.1152 0.3749 1.0000
4.000 1.0279 0.00831 0.00303 -0.1149 0.3694 1.0000
4.250 1.0529 0.00849 0.00317 -0.1144 0.3633 1.0000
4.500 1.0787 0.00861 0.00329 -0.1141 0.3583 1.0000
4.750 1.1043 0.00875 0.00341 -0.1138 0.3531 1.0000
5.000 1.1292 0.00893 0.00356 -0.1133 0.3475 1.0000
5.250 1.1549 0.00906 0.00369 -0.1130 0.3405 1.0000
5.500 1.1795 0.00927 0.00385 -0.1125 0.3325 1.0000
5.750 1.2050 0.00941 0.00399 -0.1122 0.3257 1.0000
6.000 1.2292 0.00964 0.00418 -0.1116 0.3156 1.0000
6.250 1.2540 0.00982 0.00434 -0.1112 0.3063 1.0000
6.500 1.2780 0.01005 0.00454 -0.1107 0.2946 1.0000
6.750 1.3010 0.01035 0.00476 -0.1100 0.2779 1.0000
7.000 1.3228 0.01073 0.00504 -0.1091 0.2587 1.0000
7.250 1.3422 0.01126 0.00541 -0.1078 0.2286 1.0000
7.500 1.3567 0.01212 0.00600 -0.1058 0.1853 1.0000
7.750 1.3731 0.01283 0.00655 -0.1041 0.1609 1.0000
8.000 1.3891 0.01355 0.00711 -0.1023 0.1343 1.0000
8.250 1.3792 0.01576 0.00872 -0.0963 0.0373 1.0000
8.500 1.3900 0.01665 0.00954 -0.0936 0.0209 1.0000
8.750 1.4065 0.01719 0.01012 -0.0919 0.0188 1.0000
9.000 1.4207 0.01788 0.01084 -0.0899 0.0167 1.0000
9.250 1.4369 0.01844 0.01145 -0.0883 0.0158 1.0000
9.500 1.4524 0.01905 0.01211 -0.0867 0.0149 1.0000
9.750 1.4666 0.01975 0.01284 -0.0849 0.0141 1.0000
10.000 1.4785 0.02062 0.01376 -0.0829 0.0133 1.0000
10.250 1.4858 0.02181 0.01505 -0.0803 0.0126 1.0000
10.500 1.4993 0.02261 0.01590 -0.0788 0.0123 1.0000
10.750 1.5114 0.02353 0.01688 -0.0771 0.0119 1.0000
11.000 1.5223 0.02454 0.01796 -0.0754 0.0114 1.0000
11.250 1.5326 0.02564 0.01911 -0.0737 0.0110 1.0000
11.500 1.5420 0.02683 0.02036 -0.0721 0.0106 1.0000
11.750 1.5486 0.02829 0.02187 -0.0703 0.0102 1.0000
12.000 1.5494 0.03028 0.02396 -0.0681 0.0098 1.0000
12.250 1.5399 0.03323 0.02706 -0.0654 0.0095 1.0000
12.500 1.5467 0.03487 0.02878 -0.0642 0.0094 1.0000
12.750 1.5517 0.03673 0.03071 -0.0630 0.0092 1.0000
13.000 1.5545 0.03884 0.03290 -0.0618 0.0091 1.0000
13.250 1.5558 0.04120 0.03535 -0.0607 0.0089 1.0000
13.500 1.5556 0.04383 0.03808 -0.0597 0.0087 1.0000
13.750 1.5544 0.04670 0.04104 -0.0590 0.0085 1.0000
14.000 1.5523 0.04978 0.04422 -0.0585 0.0084 1.0000
14.250 1.5498 0.05306 0.04759 -0.0582 0.0082 1.0000
14.500 1.5457 0.05662 0.05124 -0.0580 0.0081 1.0000
14.750 1.5412 0.06029 0.05500 -0.0580 0.0079 1.0000
15.000 1.5359 0.06415 0.05895 -0.0581 0.0078 1.0000
15.250 1.5292 0.06831 0.06321 -0.0584 0.0077 1.0000
15.500 1.5220 0.07257 0.06755 -0.0588 0.0076 1.0000
15.750 1.5134 0.07710 0.07218 -0.0594 0.0075 1.0000
16.000 1.5032 0.08196 0.07713 -0.0601 0.0074 1.0000
16.250 1.4914 0.08709 0.08236 -0.0610 0.0073 1.0000
16.500 1.4770 0.09250 0.08785 -0.0618 0.0072 1.0000
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Polar data table (+)
Polar graphs
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