GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.38 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe329-il-1000000-n5.txt Download as CSV file: xf-goe329-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2454 0.09138 0.08912 -0.0436 0.8176 0.0117
-8.500 -0.2388 0.08816 0.08589 -0.0455 0.8100 0.0120
-8.250 -0.2419 0.08215 0.07984 -0.0495 0.8033 0.0129
-8.000 -0.2325 0.07989 0.07758 -0.0512 0.7958 0.0130
-7.750 -0.2214 0.07756 0.07521 -0.0535 0.7881 0.0132
-7.500 -0.2070 0.07491 0.07255 -0.0568 0.7809 0.0133
-7.250 -0.1917 0.07199 0.06958 -0.0605 0.7731 0.0136
-7.000 -0.1750 0.06853 0.06609 -0.0650 0.7658 0.0139
-6.750 -0.1567 0.06485 0.06236 -0.0699 0.7580 0.0141
-6.500 -0.1364 0.06093 0.05837 -0.0749 0.7506 0.0145
-6.250 -0.1107 0.05386 0.05117 -0.0841 0.7434 0.0157
-6.000 -0.0884 0.05164 0.04889 -0.0865 0.7353 0.0158
-5.750 -0.0646 0.04910 0.04626 -0.0893 0.7255 0.0160
-5.500 -0.0393 0.04626 0.04332 -0.0923 0.7155 0.0163
-5.250 -0.0130 0.04321 0.04015 -0.0953 0.7046 0.0165
-5.000 0.0143 0.04008 0.03686 -0.0981 0.6932 0.0168
-4.750 0.0424 0.03690 0.03352 -0.1006 0.6805 0.0170
-4.500 0.0718 0.03345 0.02986 -0.1030 0.6662 0.0177
-4.250 0.1060 0.02692 0.02285 -0.1058 0.6526 0.0186
-4.000 0.1333 0.02476 0.02046 -0.1068 0.6340 0.0187
-3.750 0.1604 0.02340 0.01890 -0.1075 0.6147 0.0189
-3.500 0.1882 0.02191 0.01720 -0.1081 0.5949 0.0190
-3.250 0.2157 0.02095 0.01606 -0.1086 0.5729 0.0192
-3.000 0.2437 0.01986 0.01474 -0.1091 0.5511 0.0196
-2.750 0.2728 0.01821 0.01281 -0.1095 0.5318 0.0197
-2.500 0.3019 0.01681 0.01112 -0.1099 0.5148 0.0200
-2.250 0.3311 0.01559 0.00965 -0.1103 0.5006 0.0204
-2.000 0.3602 0.01453 0.00833 -0.1106 0.4873 0.0207
-1.750 0.3891 0.01366 0.00724 -0.1108 0.4742 0.0208
-1.500 0.4180 0.01294 0.00634 -0.1110 0.4620 0.0209
-1.250 0.4467 0.01242 0.00564 -0.1112 0.4508 0.0213
-1.000 0.4752 0.01193 0.00500 -0.1114 0.4409 0.0214
-0.750 0.5039 0.01150 0.00446 -0.1116 0.4328 0.0215
-0.500 0.5324 0.01121 0.00407 -0.1118 0.4247 0.0217
-0.250 0.5609 0.01104 0.00383 -0.1119 0.4172 0.0219
0.000 0.5891 0.01063 0.00337 -0.1122 0.4092 0.0223
0.250 0.6176 0.01047 0.00319 -0.1124 0.4022 0.0226
0.500 0.6459 0.01037 0.00306 -0.1126 0.3953 0.0229
0.750 0.6743 0.01027 0.00295 -0.1128 0.3900 0.0232
1.000 0.7028 0.01019 0.00285 -0.1130 0.3842 0.0235
1.250 0.7310 0.01014 0.00277 -0.1132 0.3785 0.0238
1.500 0.7595 0.01008 0.00270 -0.1134 0.3738 0.0242
1.750 0.7878 0.01007 0.00267 -0.1136 0.3679 0.0248
2.250 0.8443 0.01006 0.00263 -0.1140 0.3579 0.0255
2.500 0.8726 0.01007 0.00264 -0.1141 0.3533 0.0258
2.750 0.9007 0.01008 0.00263 -0.1143 0.3487 0.0264
3.000 0.9288 0.01009 0.00265 -0.1145 0.3449 0.0272
3.250 0.9569 0.01013 0.00270 -0.1147 0.3411 0.0281
3.500 0.9848 0.01020 0.00277 -0.1148 0.3366 0.0290
3.750 1.0123 0.01030 0.00285 -0.1149 0.3319 0.0300
4.000 1.0401 0.01037 0.00294 -0.1150 0.3286 0.0314
4.250 1.0679 0.01044 0.00302 -0.1151 0.3254 0.0337
4.750 1.1166 0.00909 0.00351 -0.1144 0.3180 1.0000
5.000 1.1439 0.00925 0.00364 -0.1145 0.3127 1.0000
5.250 1.1709 0.00943 0.00378 -0.1145 0.3052 1.0000
5.500 1.1977 0.00962 0.00394 -0.1145 0.2994 1.0000
5.750 1.2247 0.00978 0.00409 -0.1145 0.2927 1.0000
6.000 1.2510 0.01000 0.00428 -0.1144 0.2858 1.0000
6.250 1.2776 0.01019 0.00445 -0.1144 0.2781 1.0000
6.500 1.3034 0.01044 0.00466 -0.1143 0.2686 1.0000
6.750 1.3287 0.01073 0.00490 -0.1141 0.2563 1.0000
7.000 1.3535 0.01106 0.00516 -0.1138 0.2417 1.0000
7.250 1.3754 0.01164 0.00557 -0.1131 0.2111 1.0000
7.500 1.3812 0.01370 0.00695 -0.1100 0.1046 1.0000
7.750 1.3973 0.01473 0.00777 -0.1084 0.0662 1.0000
8.000 1.4103 0.01597 0.00875 -0.1063 0.0227 1.0000
8.250 1.4310 0.01648 0.00925 -0.1053 0.0177 1.0000
8.500 1.4515 0.01697 0.00974 -0.1044 0.0151 1.0000
8.750 1.4722 0.01740 0.01020 -0.1035 0.0140 1.0000
9.000 1.4916 0.01789 0.01071 -0.1023 0.0130 1.0000
9.250 1.5096 0.01842 0.01127 -0.1010 0.0120 1.0000
9.500 1.5263 0.01898 0.01185 -0.0994 0.0113 1.0000
9.750 1.5412 0.01949 0.01241 -0.0975 0.0109 1.0000
10.000 1.5555 0.02007 0.01304 -0.0955 0.0104 1.0000
10.250 1.5692 0.02073 0.01373 -0.0936 0.0098 1.0000
10.500 1.5820 0.02147 0.01451 -0.0917 0.0093 1.0000
10.750 1.5935 0.02233 0.01542 -0.0897 0.0089 1.0000
11.000 1.6036 0.02334 0.01648 -0.0877 0.0085 1.0000
11.250 1.6154 0.02426 0.01746 -0.0861 0.0083 1.0000
11.500 1.6264 0.02530 0.01856 -0.0845 0.0080 1.0000
11.750 1.6364 0.02645 0.01977 -0.0829 0.0078 1.0000
12.000 1.6456 0.02771 0.02110 -0.0814 0.0076 1.0000
12.250 1.6539 0.02909 0.02255 -0.0799 0.0073 1.0000
12.500 1.6614 0.03060 0.02412 -0.0785 0.0071 1.0000
12.750 1.6676 0.03226 0.02585 -0.0772 0.0069 1.0000
13.000 1.6724 0.03412 0.02778 -0.0759 0.0067 1.0000
13.250 1.6754 0.03624 0.02996 -0.0747 0.0064 1.0000
13.500 1.6746 0.03879 0.03261 -0.0735 0.0062 1.0000
13.750 1.6749 0.04134 0.03525 -0.0725 0.0061 1.0000
14.000 1.6758 0.04392 0.03792 -0.0717 0.0060 1.0000
14.250 1.6749 0.04678 0.04088 -0.0711 0.0059 1.0000
14.500 1.6725 0.04995 0.04414 -0.0707 0.0058 1.0000
14.750 1.6686 0.05345 0.04775 -0.0705 0.0058 1.0000
15.000 1.6642 0.05715 0.05155 -0.0704 0.0057 1.0000
15.250 1.6580 0.06117 0.05568 -0.0706 0.0056 1.0000
15.500 1.6508 0.06546 0.06008 -0.0710 0.0055 1.0000
15.750 1.6430 0.06993 0.06465 -0.0715 0.0054 1.0000
16.000 1.6337 0.07465 0.06948 -0.0722 0.0054 1.0000
16.250 1.6240 0.07947 0.07441 -0.0729 0.0053 1.0000
16.500 1.6139 0.08442 0.07946 -0.0737 0.0052 1.0000
16.750 1.6035 0.08944 0.08458 -0.0747 0.0052 1.0000
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Polar data table (+)
Polar graphs
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