GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.62 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe331-il-1000000-n5.txt Download as CSV file: xf-goe331-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 331 (PFALZ 60) 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 -0.1403 0.10776 0.10528 -0.0605 0.8041 0.0107
-10.250 -0.1328 0.10481 0.10229 -0.0618 0.7965 0.0111
-10.000 -0.1284 0.10079 0.09825 -0.0637 0.7900 0.0116
-9.750 -0.1187 0.09855 0.09598 -0.0649 0.7839 0.0117
-9.500 -0.1088 0.09624 0.09365 -0.0661 0.7790 0.0118
-9.250 -0.0993 0.09378 0.09118 -0.0675 0.7735 0.0120
-9.000 -0.0900 0.09127 0.08865 -0.0689 0.7674 0.0122
-8.750 -0.0809 0.08867 0.08602 -0.0704 0.7618 0.0124
-8.500 -0.0715 0.08605 0.08340 -0.0720 0.7559 0.0128
-8.250 -0.0656 0.08224 0.07957 -0.0745 0.7500 0.0137
-8.000 -0.0547 0.08011 0.07742 -0.0759 0.7443 0.0138
-7.750 -0.0437 0.07788 0.07519 -0.0776 0.7389 0.0140
-7.500 -0.0335 0.07549 0.07279 -0.0797 0.7334 0.0141
-7.250 -0.0191 0.07272 0.06998 -0.0830 0.7286 0.0143
-7.000 -0.0030 0.06975 0.06701 -0.0867 0.7240 0.0145
-6.750 0.0189 0.06474 0.06194 -0.0951 0.7188 0.0158
-6.500 0.0357 0.06253 0.05969 -0.0969 0.7128 0.0159
-6.250 0.0555 0.06020 0.05734 -0.0998 0.7071 0.0161
-6.000 0.0771 0.05775 0.05486 -0.1030 0.7011 0.0164
-5.750 0.1014 0.05512 0.05217 -0.1068 0.6957 0.0177
-5.500 0.1283 0.05164 0.04863 -0.1116 0.6914 0.0179
-5.250 0.1557 0.04832 0.04523 -0.1160 0.6860 0.0179
-5.000 0.1873 0.04448 0.04125 -0.1210 0.6796 0.0180
-4.500 0.2395 0.03891 0.03549 -0.1260 0.6644 0.0182
-4.250 0.2637 0.03719 0.03370 -0.1273 0.6578 0.0184
-4.000 0.2899 0.03541 0.03184 -0.1287 0.6508 0.0186
-3.750 0.3169 0.03359 0.02992 -0.1301 0.6435 0.0190
-3.500 0.3470 0.03152 0.02771 -0.1316 0.6338 0.0203
-3.250 0.3782 0.02905 0.02503 -0.1330 0.6237 0.0204
-2.750 0.4362 0.02469 0.02026 -0.1344 0.6001 0.0205
-2.500 0.4641 0.02287 0.01823 -0.1347 0.5870 0.0206
-2.250 0.4913 0.02135 0.01651 -0.1348 0.5735 0.0206
-2.000 0.5167 0.02006 0.01508 -0.1352 0.5599 0.0207
-1.750 0.5425 0.01932 0.01423 -0.1354 0.5465 0.0209
-1.500 0.5693 0.01844 0.01320 -0.1355 0.5323 0.0211
-1.250 0.5959 0.01778 0.01240 -0.1355 0.5177 0.0216
-0.750 0.6524 0.01494 0.00901 -0.1349 0.4914 0.0209
-0.500 0.6791 0.01443 0.00835 -0.1348 0.4758 0.0211
-0.250 0.7057 0.01390 0.00765 -0.1346 0.4574 0.0213
0.000 0.7317 0.01346 0.00699 -0.1342 0.4335 0.0215
0.250 0.7568 0.01313 0.00641 -0.1337 0.4014 0.0215
0.500 0.7814 0.01291 0.00594 -0.1330 0.3700 0.0216
0.750 0.8065 0.01277 0.00563 -0.1326 0.3490 0.0220
1.000 0.8327 0.01248 0.00520 -0.1322 0.3362 0.0220
1.250 0.8591 0.01222 0.00483 -0.1319 0.3273 0.0219
1.500 0.8857 0.01199 0.00452 -0.1317 0.3205 0.0221
1.750 0.9120 0.01185 0.00430 -0.1314 0.3139 0.0224
2.000 0.9387 0.01171 0.00412 -0.1312 0.3095 0.0227
2.250 0.9653 0.01163 0.00401 -0.1310 0.3050 0.0231
2.750 1.0175 0.01158 0.00390 -0.1305 0.2958 0.0236
3.000 1.0442 0.01157 0.00391 -0.1304 0.2928 0.0241
3.250 1.0706 0.01160 0.00394 -0.1302 0.2892 0.0247
3.500 1.0967 0.01164 0.00397 -0.1300 0.2854 0.0250
3.750 1.1225 0.01171 0.00402 -0.1298 0.2819 0.0254
4.000 1.1482 0.01179 0.00410 -0.1295 0.2785 0.0259
4.250 1.1744 0.01186 0.00418 -0.1293 0.2766 0.0263
4.500 1.2005 0.01191 0.00425 -0.1291 0.2742 0.0270
4.750 1.2261 0.01201 0.00437 -0.1288 0.2714 0.0277
5.000 1.2511 0.01215 0.00451 -0.1285 0.2679 0.0291
5.250 1.2757 0.01232 0.00467 -0.1280 0.2640 0.0298
5.500 1.3005 0.01245 0.00481 -0.1276 0.2612 0.0309
5.750 1.3255 0.01258 0.00496 -0.1272 0.2591 0.0323
6.000 1.3501 0.01273 0.00512 -0.1268 0.2562 0.0346
6.500 1.3962 0.01187 0.00581 -0.1258 0.2502 1.0000
6.750 1.4195 0.01210 0.00603 -0.1252 0.2475 1.0000
7.000 1.4426 0.01233 0.00626 -0.1245 0.2453 1.0000
7.250 1.4661 0.01252 0.00647 -0.1239 0.2439 1.0000
7.500 1.4885 0.01272 0.00669 -0.1231 0.2419 1.0000
7.750 1.5098 0.01294 0.00693 -0.1221 0.2394 1.0000
8.000 1.5307 0.01320 0.00719 -0.1211 0.2367 1.0000
8.250 1.5508 0.01349 0.00749 -0.1200 0.2337 1.0000
8.500 1.5703 0.01383 0.00782 -0.1187 0.2292 1.0000
8.750 1.5911 0.01410 0.00811 -0.1178 0.2251 1.0000
9.000 1.6108 0.01443 0.00845 -0.1167 0.2210 1.0000
9.250 1.6293 0.01482 0.00884 -0.1154 0.2168 1.0000
9.500 1.6483 0.01519 0.00923 -0.1143 0.2132 1.0000
9.750 1.6675 0.01556 0.00961 -0.1132 0.2087 1.0000
10.000 1.6847 0.01603 0.01009 -0.1118 0.2032 1.0000
10.250 1.7021 0.01651 0.01058 -0.1105 0.1987 1.0000
10.500 1.7174 0.01710 0.01115 -0.1090 0.1892 1.0000
10.750 1.7281 0.01799 0.01195 -0.1069 0.1733 1.0000
11.000 1.7342 0.01918 0.01300 -0.1042 0.1513 1.0000
11.250 1.7364 0.02067 0.01436 -0.1012 0.1299 1.0000
11.500 1.7432 0.02193 0.01557 -0.0990 0.1178 1.0000
11.750 1.7509 0.02318 0.01679 -0.0970 0.1087 1.0000
12.000 1.7602 0.02435 0.01796 -0.0953 0.1008 1.0000
12.250 1.7662 0.02581 0.01939 -0.0933 0.0902 1.0000
12.500 1.7582 0.02841 0.02182 -0.0902 0.0654 1.0000
12.750 1.7495 0.03118 0.02448 -0.0873 0.0464 1.0000
13.000 1.7486 0.03341 0.02670 -0.0853 0.0364 1.0000
13.250 1.7481 0.03566 0.02896 -0.0835 0.0289 1.0000
13.500 1.7486 0.03790 0.03121 -0.0819 0.0235 1.0000
13.750 1.7505 0.04008 0.03342 -0.0806 0.0201 1.0000
14.000 1.7531 0.04226 0.03565 -0.0795 0.0180 1.0000
14.250 1.7554 0.04450 0.03794 -0.0784 0.0166 1.0000
14.500 1.7573 0.04685 0.04035 -0.0774 0.0154 1.0000
14.750 1.7594 0.04925 0.04281 -0.0766 0.0146 1.0000
15.000 1.7600 0.05187 0.04550 -0.0758 0.0138 1.0000
15.250 1.7591 0.05472 0.04842 -0.0752 0.0130 1.0000
15.500 1.7578 0.05766 0.05145 -0.0746 0.0125 1.0000
15.750 1.7576 0.06057 0.05444 -0.0742 0.0121 1.0000
16.000 1.7560 0.06371 0.05766 -0.0739 0.0117 1.0000
16.250 1.7530 0.06708 0.06113 -0.0737 0.0114 1.0000
16.500 1.7483 0.07072 0.06485 -0.0736 0.0110 1.0000
16.750 1.7421 0.07463 0.06885 -0.0736 0.0107 1.0000
17.000 1.7342 0.07885 0.07317 -0.0738 0.0104 1.0000
17.250 1.7249 0.08336 0.07778 -0.0742 0.0101 1.0000
17.500 1.7138 0.08815 0.08267 -0.0747 0.0099 1.0000
17.750 1.7036 0.09288 0.08751 -0.0754 0.0097 1.0000
18.000 1.6932 0.09773 0.09248 -0.0762 0.0096 1.0000
18.250 1.6819 0.10279 0.09765 -0.0772 0.0095 1.0000
18.500 1.6696 0.10805 0.10302 -0.0784 0.0093 1.0000
18.750 1.6564 0.11351 0.10859 -0.0798 0.0092 1.0000
19.000 1.6436 0.11901 0.11420 -0.0813 0.0091 1.0000
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