GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 332 (PFALZ 61) AIRFOIL (goe332-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.3 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe332-il-1000000.txt Download as CSV file: xf-goe332-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 332 (PFALZ 61) 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0162 0.08528 0.08334 -0.0874 0.8867 0.0217
-9.750 -0.1284 0.09698 0.09525 -0.0749 0.9766 0.0203
-9.500 -0.1131 0.09379 0.09206 -0.0781 0.9660 0.0208
-9.250 -0.0973 0.08797 0.08618 -0.0869 0.9410 0.0228
-9.000 -0.0875 0.08353 0.08150 -0.0914 0.8864 0.0229
-8.750 -0.0829 0.08034 0.07813 -0.0930 0.8538 0.0229
-8.500 -0.0813 0.07653 0.07424 -0.0941 0.8353 0.0232
-8.250 -0.0713 0.07453 0.07217 -0.0945 0.8213 0.0233
-8.000 -0.0608 0.07247 0.07006 -0.0953 0.8093 0.0235
-7.750 -0.0510 0.07041 0.06796 -0.0965 0.7986 0.0238
-7.000 0.0271 0.04340 0.04084 -0.1101 0.7457 0.0271
-6.750 0.0329 0.03587 0.03321 -0.1180 0.7389 0.0273
-6.500 0.0472 0.03306 0.03037 -0.1199 0.7309 0.0276
-6.250 0.0643 0.03072 0.02795 -0.1217 0.7225 0.0278
-6.000 0.0833 0.02858 0.02577 -0.1235 0.7145 0.0282
-5.750 0.1029 0.02625 0.02335 -0.1256 0.7066 0.0288
-5.500 0.1206 0.01256 0.00895 -0.1374 0.7048 0.0324
-5.250 0.1431 0.01143 0.00777 -0.1378 0.6971 0.0327
-4.750 0.1901 0.00966 0.00579 -0.1384 0.6828 0.0334
-4.500 0.2170 0.01634 0.01138 -0.1449 0.6889 0.0310
-4.250 0.2430 0.01450 0.00923 -0.1450 0.6820 0.0304
-4.000 0.2695 0.01335 0.00783 -0.1449 0.6748 0.0302
-3.750 0.2968 0.01249 0.00678 -0.1449 0.6684 0.0301
-3.500 0.3242 0.01185 0.00598 -0.1448 0.6613 0.0303
-3.250 0.3516 0.01135 0.00536 -0.1447 0.6545 0.0305
-3.000 0.3795 0.01102 0.00494 -0.1446 0.6478 0.0311
-2.750 0.4070 0.01075 0.00456 -0.1445 0.6415 0.0314
-2.500 0.4351 0.01047 0.00424 -0.1445 0.6365 0.0317
-2.250 0.4632 0.01028 0.00399 -0.1445 0.6310 0.0320
-2.000 0.4903 0.00969 0.00334 -0.1444 0.6258 0.0325
-1.750 0.5181 0.00938 0.00301 -0.1444 0.6212 0.0330
-1.500 0.5463 0.00917 0.00279 -0.1445 0.6165 0.0336
-1.250 0.5741 0.00904 0.00264 -0.1444 0.6115 0.0342
-1.000 0.6019 0.00894 0.00251 -0.1444 0.6066 0.0350
-0.750 0.6303 0.00882 0.00239 -0.1445 0.6021 0.0360
-0.500 0.6584 0.00875 0.00231 -0.1445 0.5973 0.0371
-0.250 0.6861 0.00870 0.00221 -0.1444 0.5924 0.0380
0.000 0.7144 0.00856 0.00207 -0.1445 0.5879 0.0399
0.250 0.7426 0.00850 0.00202 -0.1446 0.5826 0.0420
0.500 0.7702 0.00850 0.00198 -0.1445 0.5775 0.0442
0.750 0.7982 0.00844 0.00194 -0.1445 0.5728 0.0521
1.000 0.8264 0.00828 0.00200 -0.1447 0.5677 0.1256
1.250 0.8540 0.00830 0.00204 -0.1447 0.5619 0.1438
1.500 0.8816 0.00832 0.00207 -0.1447 0.5563 0.1584
1.750 0.9095 0.00830 0.00210 -0.1447 0.5502 0.1790
2.000 0.9366 0.00799 0.00224 -0.1449 0.5441 0.3929
2.250 0.9583 0.00686 0.00244 -0.1437 0.5385 1.0000
2.500 0.9857 0.00695 0.00248 -0.1437 0.5317 1.0000
2.750 1.0126 0.00706 0.00254 -0.1435 0.5246 1.0000
3.000 1.0398 0.00716 0.00260 -0.1434 0.5159 1.0000
3.250 1.0664 0.00729 0.00268 -0.1432 0.5062 1.0000
3.500 1.0923 0.00746 0.00277 -0.1429 0.4941 1.0000
3.750 1.1185 0.00761 0.00287 -0.1426 0.4816 1.0000
4.000 1.1445 0.00777 0.00297 -0.1423 0.4700 1.0000
4.250 1.1700 0.00796 0.00311 -0.1420 0.4574 1.0000
4.500 1.1950 0.00818 0.00325 -0.1415 0.4433 1.0000
4.750 1.2197 0.00842 0.00341 -0.1410 0.4298 1.0000
5.000 1.2446 0.00864 0.00358 -0.1406 0.4175 1.0000
5.250 1.2699 0.00884 0.00374 -0.1402 0.4075 1.0000
5.500 1.2945 0.00907 0.00393 -0.1397 0.3977 1.0000
5.750 1.3191 0.00929 0.00411 -0.1392 0.3880 1.0000
6.000 1.3437 0.00950 0.00431 -0.1387 0.3793 1.0000
6.250 1.3671 0.00978 0.00453 -0.1380 0.3688 1.0000
6.500 1.3906 0.01005 0.00475 -0.1374 0.3565 1.0000
6.750 1.4137 0.01032 0.00499 -0.1367 0.3449 1.0000
7.000 1.4362 0.01062 0.00525 -0.1359 0.3343 1.0000
7.250 1.4582 0.01093 0.00551 -0.1349 0.3233 1.0000
7.500 1.4810 0.01119 0.00576 -0.1342 0.3145 1.0000
7.750 1.5020 0.01152 0.00605 -0.1331 0.3048 1.0000
8.000 1.5226 0.01185 0.00635 -0.1320 0.2932 1.0000
8.250 1.5427 0.01216 0.00664 -0.1307 0.2831 1.0000
8.500 1.5607 0.01253 0.00698 -0.1291 0.2724 1.0000
8.750 1.5774 0.01296 0.00736 -0.1273 0.2592 1.0000
9.000 1.5930 0.01347 0.00780 -0.1253 0.2426 1.0000
9.250 1.6025 0.01426 0.00844 -0.1223 0.2161 1.0000
9.500 1.6100 0.01517 0.00919 -0.1191 0.1892 1.0000
9.750 1.6176 0.01611 0.01001 -0.1160 0.1674 1.0000
10.000 1.6237 0.01715 0.01094 -0.1129 0.1474 1.0000
10.250 1.6267 0.01840 0.01205 -0.1094 0.1219 1.0000
10.500 1.6206 0.02027 0.01371 -0.1050 0.0893 1.0000
10.750 1.6209 0.02190 0.01524 -0.1017 0.0726 1.0000
11.000 1.6103 0.02441 0.01756 -0.0976 0.0390 1.0000
11.250 1.6062 0.02667 0.01978 -0.0945 0.0253 1.0000
11.500 1.6114 0.02833 0.02147 -0.0927 0.0220 1.0000
11.750 1.6186 0.02987 0.02306 -0.0911 0.0203 1.0000
12.000 1.6231 0.03169 0.02492 -0.0895 0.0188 1.0000
12.250 1.6298 0.03337 0.02666 -0.0881 0.0180 1.0000
12.500 1.6366 0.03508 0.02844 -0.0869 0.0173 1.0000
12.750 1.6416 0.03697 0.03039 -0.0856 0.0166 1.0000
13.000 1.6447 0.03910 0.03257 -0.0843 0.0160 1.0000
13.250 1.6442 0.04165 0.03521 -0.0830 0.0153 1.0000
13.500 1.6471 0.04392 0.03755 -0.0819 0.0148 1.0000
13.750 1.6510 0.04613 0.03983 -0.0810 0.0145 1.0000
14.000 1.6536 0.04852 0.04230 -0.0802 0.0141 1.0000
14.250 1.6551 0.05108 0.04494 -0.0794 0.0137 1.0000
14.500 1.6559 0.05380 0.04772 -0.0787 0.0134 1.0000
14.750 1.6548 0.05675 0.05075 -0.0781 0.0131 1.0000
15.000 1.6511 0.06006 0.05414 -0.0775 0.0127 1.0000
15.250 1.6446 0.06381 0.05798 -0.0770 0.0125 1.0000
15.500 1.6333 0.06824 0.06252 -0.0766 0.0122 1.0000
15.750 1.6304 0.07166 0.06604 -0.0763 0.0120 1.0000
16.000 1.6279 0.07507 0.06954 -0.0762 0.0119 1.0000
16.250 1.6245 0.07867 0.07323 -0.0762 0.0117 1.0000
16.500 1.6201 0.08245 0.07709 -0.0763 0.0115 1.0000
16.750 1.6150 0.08636 0.08110 -0.0765 0.0113 1.0000
17.000 1.6093 0.09037 0.08519 -0.0768 0.0112 1.0000
17.250 1.6036 0.09444 0.08935 -0.0772 0.0110 1.0000
17.500 1.5972 0.09869 0.09369 -0.0777 0.0108 1.0000
17.750 1.5906 0.10301 0.09809 -0.0784 0.0106 1.0000
18.000 1.5835 0.10742 0.10258 -0.0792 0.0105 1.0000
18.250 1.5760 0.11192 0.10716 -0.0801 0.0103 1.0000
18.500 1.5674 0.11664 0.11197 -0.0812 0.0102 1.0000
18.750 1.5572 0.12166 0.11707 -0.0825 0.0100 1.0000
19.000 1.5458 0.12694 0.12244 -0.0840 0.0099 1.0000
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