GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.66 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe329-il-1000000.txt Download as CSV file: xf-goe329-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 329 (PFALZ 58) 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 -0.1606 0.09716 0.09546 -0.0471 0.9143 0.0152
-9.750 -0.1558 0.09432 0.09257 -0.0476 0.9023 0.0154
-8.250 -0.2174 0.08887 0.08697 -0.0463 0.8825 0.0168
-8.000 -0.2117 0.08528 0.08334 -0.0501 0.8708 0.0175
-7.750 -0.2069 0.08151 0.07952 -0.0555 0.8601 0.0176
-7.500 -0.1345 0.06262 0.06060 -0.0619 0.8291 0.0178
-7.250 -0.1264 0.05935 0.05731 -0.0620 0.8226 0.0179
-7.000 -0.1168 0.05625 0.05417 -0.0635 0.8161 0.0180
-6.750 -0.1058 0.05299 0.05090 -0.0659 0.8099 0.0181
-6.500 -0.0935 0.04962 0.04750 -0.0689 0.8033 0.0183
-6.250 -0.0791 0.04627 0.04410 -0.0721 0.7973 0.0186
-6.000 -0.0937 0.05726 0.05495 -0.0802 0.8091 0.0186
-5.750 -0.0708 0.05421 0.05183 -0.0838 0.8022 0.0192
-5.500 -0.0453 0.05081 0.04834 -0.0878 0.7959 0.0201
-5.250 -0.0044 0.04547 0.04277 -0.0952 0.7893 0.0211
-5.000 0.0241 0.04178 0.03892 -0.0982 0.7828 0.0212
-4.750 0.0524 0.03823 0.03521 -0.1005 0.7756 0.0212
-4.250 0.0982 0.03240 0.02917 -0.1037 0.7606 0.0218
-4.000 0.1241 0.03062 0.02727 -0.1047 0.7526 0.0221
-3.750 0.1515 0.02876 0.02531 -0.1058 0.7436 0.0225
-3.500 0.1797 0.02683 0.02322 -0.1067 0.7341 0.0232
-3.250 0.2131 0.02452 0.02061 -0.1072 0.7235 0.0251
-3.000 0.2440 0.02272 0.01850 -0.1077 0.7123 0.0253
-2.750 0.2731 0.02109 0.01659 -0.1081 0.7002 0.0253
-2.500 0.3004 0.01794 0.01323 -0.1093 0.6868 0.0259
-2.250 0.3282 0.01700 0.01215 -0.1098 0.6699 0.0263
-2.000 0.3562 0.01621 0.01121 -0.1101 0.6497 0.0268
-1.750 0.3845 0.01546 0.01025 -0.1104 0.6283 0.0278
-1.500 0.4142 0.01554 0.01002 -0.1101 0.6053 0.0301
-1.250 0.4428 0.01518 0.00938 -0.1102 0.5823 0.0302
-1.000 0.4711 0.01311 0.00712 -0.1108 0.5608 0.0313
-0.750 0.4990 0.01268 0.00656 -0.1111 0.5391 0.0320
-0.500 -1.1691 0.01350 0.01030 0.2642 0.6123 0.0353
-0.250 0.5554 0.01223 0.00582 -0.1113 0.5027 0.0350
0.000 0.5840 0.01171 0.00509 -0.1114 0.4883 0.0375
0.250 0.6121 0.01132 0.00468 -0.1116 0.4751 0.0388
0.500 0.6404 0.01112 0.00443 -0.1118 0.4634 0.0408
0.750 0.6686 0.01083 0.00406 -0.1120 0.4528 0.0463
1.000 0.6965 0.01071 0.00391 -0.1121 0.4421 0.0499
1.250 0.7260 0.01004 0.00311 -0.1119 0.4334 0.0337
1.500 0.7543 0.00989 0.00291 -0.1121 0.4249 0.0329
1.750 0.7827 0.00979 0.00279 -0.1123 0.4172 0.0328
2.000 0.8109 0.00977 0.00273 -0.1124 0.4099 0.0334
2.250 0.8394 0.00971 0.00265 -0.1126 0.4033 0.0332
2.500 0.8674 0.00974 0.00263 -0.1128 0.3962 0.0335
2.750 0.8958 0.00972 0.00262 -0.1130 0.3904 0.0343
3.000 0.9238 0.00977 0.00264 -0.1131 0.3840 0.0356
3.250 0.9517 0.00984 0.00269 -0.1132 0.3784 0.0366
3.500 0.9798 0.00988 0.00272 -0.1133 0.3734 0.0389
3.750 1.0074 0.00997 0.00280 -0.1134 0.3681 0.0439
4.000 1.0283 0.00843 0.00314 -0.1125 0.3636 1.0000
4.250 1.0563 0.00854 0.00324 -0.1127 0.3592 1.0000
4.500 1.0838 0.00870 0.00335 -0.1128 0.3543 1.0000
4.750 1.1108 0.00890 0.00351 -0.1128 0.3492 1.0000
5.000 1.1387 0.00900 0.00363 -0.1129 0.3452 1.0000
5.250 1.1659 0.00916 0.00376 -0.1130 0.3391 1.0000
5.500 1.1928 0.00934 0.00391 -0.1130 0.3317 1.0000
5.750 1.2200 0.00949 0.00406 -0.1130 0.3251 1.0000
6.000 1.2464 0.00971 0.00424 -0.1130 0.3184 1.0000
6.250 1.2735 0.00985 0.00438 -0.1130 0.3120 1.0000
6.500 1.2997 0.01006 0.00457 -0.1129 0.3058 1.0000
6.750 1.3264 0.01023 0.00475 -0.1129 0.2990 1.0000
7.000 1.3520 0.01049 0.00497 -0.1128 0.2896 1.0000
7.250 1.3780 0.01070 0.00516 -0.1127 0.2791 1.0000
7.500 1.4028 0.01101 0.00542 -0.1124 0.2640 1.0000
7.750 1.4257 0.01148 0.00576 -0.1118 0.2379 1.0000
8.000 1.4308 0.01355 0.00710 -0.1086 0.1287 1.0000
8.250 1.4297 0.01604 0.00894 -0.1044 0.0285 1.0000
8.500 1.4486 0.01670 0.00958 -0.1032 0.0216 1.0000
8.750 1.4670 0.01734 0.01024 -0.1018 0.0187 1.0000
9.000 1.4865 0.01784 0.01078 -0.1007 0.0177 1.0000
9.250 1.5046 0.01840 0.01138 -0.0993 0.0167 1.0000
9.500 1.5202 0.01904 0.01205 -0.0976 0.0157 1.0000
9.750 1.5293 0.01990 0.01299 -0.0947 0.0148 1.0000
10.000 1.5413 0.02063 0.01378 -0.0924 0.0143 1.0000
10.250 1.5543 0.02135 0.01455 -0.0904 0.0139 1.0000
10.500 1.5662 0.02217 0.01542 -0.0884 0.0133 1.0000
10.750 1.5768 0.02311 0.01642 -0.0864 0.0129 1.0000
11.000 1.5862 0.02419 0.01757 -0.0844 0.0124 1.0000
11.250 1.5929 0.02553 0.01897 -0.0823 0.0121 1.0000
11.500 1.5942 0.02736 0.02090 -0.0799 0.0117 1.0000
11.750 1.5902 0.02976 0.02343 -0.0773 0.0113 1.0000
12.000 1.5978 0.03131 0.02505 -0.0760 0.0112 1.0000
12.250 1.6031 0.03311 0.02693 -0.0747 0.0110 1.0000
12.500 1.6066 0.03515 0.02907 -0.0734 0.0108 1.0000
12.750 1.6086 0.03744 0.03145 -0.0722 0.0106 1.0000
13.000 1.6090 0.03996 0.03406 -0.0712 0.0104 1.0000
13.250 1.6083 0.04272 0.03690 -0.0703 0.0102 1.0000
13.500 1.6076 0.04559 0.03986 -0.0697 0.0099 1.0000
13.750 1.6047 0.04880 0.04316 -0.0692 0.0098 1.0000
14.000 1.6017 0.05216 0.04661 -0.0689 0.0096 1.0000
14.250 1.5968 0.05593 0.05047 -0.0689 0.0094 1.0000
14.500 1.5899 0.06007 0.05470 -0.0691 0.0093 1.0000
14.750 1.5809 0.06460 0.05933 -0.0694 0.0092 1.0000
15.000 1.5699 0.06951 0.06434 -0.0700 0.0091 1.0000
15.250 1.5567 0.07478 0.06972 -0.0706 0.0089 1.0000
15.500 1.5419 0.08023 0.07527 -0.0713 0.0088 1.0000
15.750 1.5251 0.08590 0.08105 -0.0719 0.0087 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 329 (PFALZ 58) AIRFOIL (goe329-il)