GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.9 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe330-il-1000000-n5.txt Download as CSV file: xf-goe330-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2243 0.10314 0.10137 -0.0578 0.9402 0.0075
-10.250 -0.2202 0.09986 0.09804 -0.0589 0.9239 0.0078
-10.000 -0.2267 0.09393 0.09205 -0.0610 0.9060 0.0088
-9.750 -0.2193 0.09152 0.08957 -0.0621 0.8904 0.0090
-9.500 -0.2115 0.08910 0.08709 -0.0632 0.8765 0.0091
-9.250 -0.2036 0.08659 0.08452 -0.0645 0.8636 0.0093
-9.000 -0.1962 0.08388 0.08176 -0.0660 0.8521 0.0096
-8.750 -0.1896 0.08089 0.07871 -0.0678 0.8418 0.0099
-8.250 -0.1893 0.07073 0.06851 -0.0761 0.8262 0.0116
-8.000 -0.1740 0.06824 0.06600 -0.0794 0.8199 0.0118
-7.750 -0.1577 0.06554 0.06325 -0.0830 0.8136 0.0120
-7.500 -0.1403 0.06229 0.05998 -0.0875 0.8079 0.0123
-7.250 -0.1244 0.04983 0.04739 -0.1042 0.8023 0.0146
-7.000 -0.1013 0.04753 0.04501 -0.1073 0.7963 0.0148
-6.750 -0.0771 0.04513 0.04256 -0.1103 0.7909 0.0151
-6.500 -0.0592 0.02584 0.02251 -0.1243 0.7863 0.0185
-6.250 -0.0351 0.02412 0.02062 -0.1248 0.7807 0.0188
-6.000 -0.0102 0.02264 0.01902 -0.1251 0.7751 0.0191
-5.750 0.0139 0.02077 0.01694 -0.1253 0.7679 0.0195
-5.500 0.0375 0.01855 0.01448 -0.1254 0.7599 0.0202
-5.250 0.0585 0.01498 0.01038 -0.1251 0.7504 0.0212
-5.000 0.0837 0.01374 0.00889 -0.1249 0.7397 0.0217
-4.750 0.1096 0.01305 0.00800 -0.1246 0.7262 0.0222
-4.500 0.1354 0.01263 0.00738 -0.1242 0.7054 0.0226
-4.250 0.1606 0.01223 0.00676 -0.1238 0.6795 0.0228
-4.000 0.1859 0.01194 0.00627 -0.1233 0.6574 0.0229
-3.750 0.2120 0.01165 0.00583 -0.1229 0.6419 0.0231
-3.500 0.2383 0.01130 0.00534 -0.1227 0.6301 0.0232
-3.250 0.2642 0.01052 0.00440 -0.1224 0.6210 0.0235
-2.750 0.3175 0.00979 0.00349 -0.1220 0.6053 0.0241
-2.500 0.3444 0.00956 0.00319 -0.1218 0.5981 0.0243
-2.250 0.3716 0.00936 0.00295 -0.1216 0.5913 0.0246
-2.000 0.3987 0.00924 0.00278 -0.1215 0.5827 0.0251
-1.750 0.4259 0.00910 0.00260 -0.1213 0.5743 0.0255
-1.500 0.4527 0.00899 0.00243 -0.1211 0.5632 0.0258
-1.250 0.4794 0.00892 0.00228 -0.1209 0.5487 0.0262
-1.000 0.5060 0.00887 0.00215 -0.1206 0.5301 0.0267
-0.750 0.5318 0.00890 0.00206 -0.1202 0.5037 0.0272
-0.500 0.5569 0.00901 0.00201 -0.1197 0.4722 0.0277
-0.250 0.5823 0.00912 0.00199 -0.1193 0.4471 0.0281
0.000 0.6082 0.00921 0.00198 -0.1189 0.4295 0.0285
0.250 0.6346 0.00926 0.00197 -0.1187 0.4169 0.0288
0.500 0.6610 0.00932 0.00197 -0.1184 0.4057 0.0291
1.000 0.7145 0.00941 0.00198 -0.1181 0.3894 0.0297
1.250 0.7413 0.00945 0.00198 -0.1179 0.3828 0.0312
1.500 0.7682 0.00949 0.00201 -0.1177 0.3771 0.0334
1.750 0.7952 0.00953 0.00205 -0.1176 0.3711 0.0360
2.000 0.8217 0.00958 0.00213 -0.1174 0.3652 0.0528
2.250 0.8487 0.00964 0.00221 -0.1173 0.3609 0.0667
2.500 0.8756 0.00969 0.00228 -0.1172 0.3561 0.0733
2.750 0.9022 0.00978 0.00235 -0.1170 0.3512 0.0769
3.000 0.9287 0.00987 0.00244 -0.1169 0.3463 0.0803
3.250 0.9554 0.00995 0.00253 -0.1167 0.3407 0.0863
3.500 0.9811 0.00972 0.00272 -0.1166 0.3351 0.3246
4.000 1.0366 0.00873 0.00315 -0.1172 0.3254 1.0000
4.250 1.0620 0.00889 0.00327 -0.1168 0.3199 1.0000
4.500 1.0874 0.00904 0.00340 -0.1165 0.3145 1.0000
4.750 1.1129 0.00919 0.00353 -0.1161 0.3080 1.0000
5.000 1.1377 0.00938 0.00368 -0.1157 0.3015 1.0000
5.250 1.1629 0.00954 0.00383 -0.1153 0.2942 1.0000
5.500 1.1867 0.00981 0.00402 -0.1147 0.2800 1.0000
5.750 1.2092 0.01015 0.00425 -0.1139 0.2602 1.0000
6.000 1.2313 0.01052 0.00451 -0.1130 0.2399 1.0000
6.250 1.2511 0.01105 0.00488 -0.1118 0.2101 1.0000
6.500 1.2699 0.01165 0.00531 -0.1105 0.1820 1.0000
6.750 1.2907 0.01209 0.00566 -0.1094 0.1676 1.0000
7.000 1.3119 0.01249 0.00601 -0.1084 0.1564 1.0000
7.250 1.3330 0.01287 0.00636 -0.1075 0.1470 1.0000
7.500 1.3539 0.01327 0.00671 -0.1065 0.1354 1.0000
7.750 1.3623 0.01443 0.00753 -0.1035 0.0830 1.0000
8.250 1.3788 0.01650 0.00929 -0.0973 0.0179 1.0000
8.500 1.3958 0.01702 0.00982 -0.0957 0.0150 1.0000
8.750 1.4132 0.01749 0.01032 -0.0943 0.0133 1.0000
9.000 1.4304 0.01800 0.01085 -0.0928 0.0122 1.0000
9.250 1.4464 0.01857 0.01144 -0.0913 0.0112 1.0000
9.500 1.4614 0.01922 0.01212 -0.0896 0.0101 1.0000
9.750 1.4773 0.01980 0.01275 -0.0881 0.0097 1.0000
10.000 1.4928 0.02043 0.01342 -0.0866 0.0091 1.0000
10.250 1.5074 0.02113 0.01415 -0.0851 0.0085 1.0000
10.500 1.5209 0.02191 0.01496 -0.0835 0.0079 1.0000
10.750 1.5328 0.02282 0.01592 -0.0818 0.0074 1.0000
11.000 1.5450 0.02374 0.01689 -0.0802 0.0071 1.0000
11.250 1.5573 0.02467 0.01788 -0.0787 0.0069 1.0000
11.500 1.5688 0.02568 0.01895 -0.0772 0.0066 1.0000
11.750 1.5793 0.02678 0.02010 -0.0757 0.0063 1.0000
12.000 1.5893 0.02797 0.02135 -0.0742 0.0061 1.0000
12.250 1.5984 0.02925 0.02269 -0.0727 0.0058 1.0000
12.500 1.6061 0.03067 0.02416 -0.0713 0.0056 1.0000
12.750 1.6119 0.03229 0.02585 -0.0697 0.0053 1.0000
13.000 1.6152 0.03419 0.02783 -0.0682 0.0051 1.0000
13.250 1.6215 0.03587 0.02958 -0.0669 0.0050 1.0000
13.500 1.6261 0.03774 0.03153 -0.0657 0.0049 1.0000
13.750 1.6296 0.03980 0.03367 -0.0646 0.0047 1.0000
14.000 1.6318 0.04207 0.03603 -0.0636 0.0046 1.0000
14.250 1.6334 0.04449 0.03854 -0.0628 0.0045 1.0000
14.500 1.6337 0.04717 0.04131 -0.0621 0.0044 1.0000
14.750 1.6333 0.05003 0.04426 -0.0615 0.0043 1.0000
15.000 1.6320 0.05309 0.04742 -0.0612 0.0042 1.0000
15.250 1.6295 0.05637 0.05079 -0.0610 0.0041 1.0000
15.500 1.6258 0.05988 0.05439 -0.0609 0.0040 1.0000
15.750 1.6211 0.06360 0.05821 -0.0609 0.0040 1.0000
16.000 1.6146 0.06764 0.06235 -0.0612 0.0039 1.0000
16.250 1.6062 0.07201 0.06682 -0.0615 0.0039 1.0000
16.500 1.5973 0.07653 0.07144 -0.0621 0.0038 1.0000
16.750 1.5867 0.08143 0.07645 -0.0628 0.0037 1.0000
17.000 1.5753 0.08656 0.08169 -0.0638 0.0037 1.0000
17.250 1.5623 0.09197 0.08721 -0.0649 0.0036 1.0000
17.500 1.5490 0.09750 0.09285 -0.0662 0.0036 1.0000
17.750 1.5345 0.10332 0.09878 -0.0677 0.0035 1.0000
18.000 1.5204 0.10909 0.10466 -0.0692 0.0035 1.0000
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Polar data table (+)
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