GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Reynolds number: 500,000 Max Cl/Cd: 101.56 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe330-il-500000-n5.txt Download as CSV file: xf-goe330-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1654 0.08847 0.08608 -0.0681 0.9335 0.0122
-8.750 -0.1587 0.08558 0.08317 -0.0695 0.9198 0.0125
-8.500 -0.1524 0.08263 0.08017 -0.0709 0.9062 0.0131
-8.250 -0.1482 0.07897 0.07648 -0.0730 0.8934 0.0139
-8.000 -0.1520 0.07298 0.07044 -0.0778 0.8804 0.0146
-7.750 -0.1392 0.07077 0.06818 -0.0799 0.8707 0.0149
-7.500 -0.1249 0.06840 0.06577 -0.0826 0.8610 0.0151
-7.250 -0.1095 0.06554 0.06286 -0.0860 0.8526 0.0155
-7.000 -0.0926 0.06220 0.05945 -0.0904 0.8447 0.0161
-6.750 -0.0733 0.05768 0.05486 -0.0966 0.8374 0.0172
-6.500 -0.0494 0.04821 0.04521 -0.1090 0.8301 0.0186
-6.250 -0.0269 0.04614 0.04306 -0.1113 0.8237 0.0190
-6.000 -0.0036 0.04396 0.04080 -0.1135 0.8169 0.0194
-5.750 0.0209 0.04128 0.03800 -0.1162 0.8111 0.0203
-5.500 0.0473 0.03653 0.03304 -0.1202 0.8049 0.0214
-5.250 0.0724 0.02621 0.02204 -0.1249 0.7992 0.0235
-5.000 0.0964 0.02470 0.02036 -0.1253 0.7925 0.0239
-4.750 0.1208 0.02294 0.01839 -0.1255 0.7848 0.0243
-4.500 0.1454 0.02117 0.01639 -0.1255 0.7775 0.0248
-4.250 0.1700 0.01920 0.01414 -0.1254 0.7688 0.0253
-4.000 0.1952 0.01769 0.01237 -0.1252 0.7600 0.0261
-3.750 0.2201 0.01585 0.01018 -0.1248 0.7497 0.0269
-3.500 0.2456 0.01458 0.00861 -0.1244 0.7363 0.0273
-3.250 0.2713 0.01369 0.00748 -0.1240 0.7209 0.0277
-3.000 0.2971 0.01302 0.00659 -0.1236 0.7044 0.0281
-2.750 0.3229 0.01249 0.00585 -0.1231 0.6877 0.0283
-2.500 0.3486 0.01208 0.00526 -0.1227 0.6716 0.0286
-2.250 0.3744 0.01183 0.00485 -0.1222 0.6566 0.0290
-2.000 0.4004 0.01163 0.00451 -0.1218 0.6435 0.0293
-1.750 0.4266 0.01133 0.00410 -0.1214 0.6324 0.0295
-1.500 0.4525 0.01087 0.00353 -0.1211 0.6232 0.0300
-1.250 0.4785 0.01057 0.00315 -0.1207 0.6139 0.0306
-1.000 0.5050 0.01037 0.00289 -0.1204 0.6046 0.0312
-0.750 0.5312 0.01026 0.00272 -0.1201 0.5951 0.0318
-0.500 0.5578 0.01016 0.00258 -0.1198 0.5843 0.0325
-0.250 0.5842 0.01010 0.00247 -0.1195 0.5721 0.0332
0.000 0.6104 0.01008 0.00238 -0.1192 0.5578 0.0339
0.250 0.6364 0.01008 0.00231 -0.1188 0.5407 0.0347
0.500 0.6620 0.01013 0.00227 -0.1184 0.5199 0.0360
0.750 0.6869 0.01023 0.00225 -0.1178 0.4940 0.0373
1.000 0.7112 0.01039 0.00227 -0.1172 0.4686 0.0389
1.250 0.7357 0.01055 0.00233 -0.1166 0.4477 0.0430
1.500 0.7606 0.01069 0.00246 -0.1161 0.4315 0.0576
1.750 0.7860 0.01084 0.00256 -0.1157 0.4196 0.0709
2.000 0.8115 0.01099 0.00265 -0.1153 0.4104 0.0777
2.250 0.8375 0.01107 0.00273 -0.1150 0.4029 0.0866
2.750 0.8782 0.00968 0.00320 -0.1126 0.3904 0.8515
3.250 0.9452 0.00996 0.00347 -0.1153 0.3781 1.0000
3.500 0.9706 0.01011 0.00358 -0.1149 0.3722 1.0000
3.750 0.9954 0.01030 0.00372 -0.1144 0.3662 1.0000
4.000 1.0204 0.01047 0.00387 -0.1139 0.3615 1.0000
4.250 1.0457 0.01062 0.00401 -0.1135 0.3561 1.0000
4.500 1.0703 0.01082 0.00418 -0.1130 0.3508 1.0000
4.750 1.0951 0.01100 0.00436 -0.1125 0.3460 1.0000
5.000 1.1200 0.01117 0.00452 -0.1121 0.3404 1.0000
5.250 1.1443 0.01138 0.00471 -0.1115 0.3349 1.0000
5.500 1.1687 0.01157 0.00492 -0.1110 0.3302 1.0000
5.750 1.1933 0.01175 0.00512 -0.1106 0.3251 1.0000
6.000 1.2168 0.01200 0.00534 -0.1099 0.3182 1.0000
6.250 1.2400 0.01225 0.00557 -0.1092 0.3062 1.0000
6.500 1.2622 0.01256 0.00583 -0.1084 0.2918 1.0000
6.750 1.2838 0.01289 0.00611 -0.1075 0.2768 1.0000
7.000 1.3040 0.01331 0.00644 -0.1064 0.2580 1.0000
7.250 1.3214 0.01390 0.00688 -0.1048 0.2272 1.0000
7.500 1.3348 0.01471 0.00746 -0.1027 0.1912 1.0000
7.750 1.3493 0.01539 0.00803 -0.1006 0.1722 1.0000
8.000 1.3648 0.01601 0.00858 -0.0987 0.1592 1.0000
8.250 1.3797 0.01666 0.00917 -0.0968 0.1438 1.0000
8.500 1.3885 0.01771 0.01000 -0.0942 0.1024 1.0000
9.000 1.3890 0.02096 0.01282 -0.0866 0.0209 1.0000
9.250 1.4029 0.02172 0.01363 -0.0849 0.0178 1.0000
9.500 1.4164 0.02253 0.01449 -0.0832 0.0160 1.0000
9.750 1.4280 0.02348 0.01549 -0.0814 0.0143 1.0000
10.000 1.4407 0.02438 0.01647 -0.0797 0.0133 1.0000
10.250 1.4529 0.02532 0.01749 -0.0781 0.0125 1.0000
10.500 1.4640 0.02638 0.01863 -0.0765 0.0118 1.0000
10.750 1.4736 0.02757 0.01989 -0.0748 0.0112 1.0000
11.000 1.4810 0.02898 0.02137 -0.0730 0.0106 1.0000
11.250 1.4853 0.03069 0.02317 -0.0711 0.0100 1.0000
11.500 1.4938 0.03209 0.02467 -0.0697 0.0097 1.0000
11.750 1.5007 0.03365 0.02632 -0.0683 0.0093 1.0000
12.000 1.5067 0.03536 0.02812 -0.0669 0.0089 1.0000
12.250 1.5112 0.03723 0.03008 -0.0655 0.0085 1.0000
12.500 1.5141 0.03932 0.03226 -0.0643 0.0082 1.0000
12.750 1.5158 0.04161 0.03465 -0.0631 0.0080 1.0000
13.000 1.5159 0.04416 0.03729 -0.0621 0.0078 1.0000
13.250 1.5134 0.04712 0.04035 -0.0613 0.0076 1.0000
13.500 1.5075 0.05063 0.04399 -0.0606 0.0074 1.0000
13.750 1.5006 0.05444 0.04792 -0.0602 0.0072 1.0000
14.000 1.4972 0.05792 0.05152 -0.0601 0.0071 1.0000
14.250 1.4926 0.06165 0.05538 -0.0600 0.0070 1.0000
14.500 1.4866 0.06567 0.05952 -0.0602 0.0069 1.0000
14.750 1.4799 0.06986 0.06383 -0.0605 0.0068 1.0000
15.000 1.4722 0.07427 0.06836 -0.0610 0.0067 1.0000
15.250 1.4646 0.07879 0.07299 -0.0616 0.0065 1.0000
15.500 1.4568 0.08343 0.07775 -0.0624 0.0064 1.0000
15.750 1.4490 0.08811 0.08254 -0.0633 0.0063 1.0000
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Polar data table (+)
Polar graphs
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