GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.89 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe331-il-1000000.txt Download as CSV file: xf-goe331-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1172 0.10371 0.10192 -0.0644 0.9322 0.0152
-9.750 -0.1116 0.10113 0.09927 -0.0648 0.9081 0.0157
-9.500 -0.1059 0.09845 0.09646 -0.0656 0.8767 0.0160
-9.250 -0.0996 0.09570 0.09358 -0.0672 0.8533 0.0160
-9.000 -0.0943 0.09290 0.09069 -0.0698 0.8375 0.0161
-8.750 -0.0887 0.09001 0.08773 -0.0725 0.8259 0.0161
-8.500 -0.0798 0.08673 0.08441 -0.0731 0.8169 0.0162
-8.250 -0.0697 0.08402 0.08166 -0.0734 0.8090 0.0163
-8.000 -0.0598 0.08152 0.07914 -0.0745 0.8013 0.0164
-7.750 -0.0499 0.07911 0.07669 -0.0759 0.7944 0.0165
-7.500 -0.0400 0.07670 0.07427 -0.0777 0.7883 0.0167
-7.250 -0.0271 0.07411 0.07165 -0.0805 0.7822 0.0169
-7.000 -0.0117 0.07134 0.06886 -0.0839 0.7766 0.0171
-6.750 0.0054 0.06843 0.06593 -0.0877 0.7713 0.0175
-6.500 0.0245 0.06540 0.06286 -0.0918 0.7659 0.0182
-6.250 0.0534 0.06141 0.05879 -0.1001 0.7607 0.0188
-6.000 0.0834 0.05734 0.05465 -0.1079 0.7561 0.0189
-5.750 0.1109 0.05367 0.05089 -0.1129 0.7508 0.0189
-5.500 0.1316 0.05026 0.04740 -0.1155 0.7455 0.0190
-5.250 0.1500 0.04786 0.04499 -0.1163 0.7407 0.0191
-5.000 0.1716 0.04560 0.04271 -0.1179 0.7356 0.0192
-4.750 0.1954 0.04340 0.04044 -0.1199 0.7307 0.0194
-4.500 0.2213 0.04113 0.03809 -0.1221 0.7257 0.0197
-4.250 0.2487 0.03878 0.03568 -0.1244 0.7202 0.0201
-4.000 0.2769 0.03645 0.03323 -0.1264 0.7143 0.0208
-3.750 0.3150 0.03363 0.03018 -0.1291 0.7091 0.0217
-3.500 0.3461 0.03118 0.02757 -0.1306 0.7036 0.0218
-3.250 0.3752 0.02897 0.02519 -0.1315 0.6977 0.0218
-3.000 0.3987 0.02646 0.02259 -0.1324 0.6919 0.0220
-2.750 0.4241 0.02498 0.02105 -0.1331 0.6848 0.0222
-2.500 0.4500 0.02368 0.01963 -0.1335 0.6770 0.0224
-2.250 0.4773 0.02237 0.01823 -0.1340 0.6692 0.0227
-2.000 0.5049 0.02110 0.01683 -0.1342 0.6618 0.0233
-1.750 0.5378 0.01972 0.01518 -0.1339 0.6550 0.0250
-1.500 0.5668 0.01856 0.01375 -0.1337 0.6469 0.0251
-1.250 0.5937 0.01671 0.01176 -0.1340 0.6387 0.0253
-0.750 0.6470 0.01510 0.00998 -0.1344 0.6174 0.0259
-0.500 0.6742 0.01444 0.00921 -0.1344 0.6062 0.0263
-0.250 0.7015 0.01380 0.00842 -0.1342 0.5943 0.0270
0.000 0.1236 0.00831 0.00512 -0.0073 0.5728 0.1270
0.250 0.7575 0.01237 0.00655 -0.1336 0.5685 0.0293
0.500 0.7840 0.01196 0.00607 -0.1335 0.5545 0.0299
0.750 0.8106 0.01167 0.00566 -0.1333 0.5393 0.0312
1.000 0.8376 0.01142 0.00517 -0.1329 0.5225 0.0335
1.250 0.8634 0.01111 0.00480 -0.1326 0.5039 0.0343
1.500 0.8889 0.01101 0.00459 -0.1323 0.4830 0.0357
3.750 1.1125 0.01123 0.00387 -0.1276 0.3157 0.0349
4.000 1.1383 0.01132 0.00394 -0.1273 0.3107 0.0359
4.250 1.1634 0.01145 0.00405 -0.1269 0.3055 0.0357
4.500 1.1888 0.01157 0.00416 -0.1265 0.3014 0.0361
4.750 1.2149 0.01165 0.00426 -0.1263 0.2984 0.0371
5.000 1.2402 0.01177 0.00438 -0.1260 0.2950 0.0386
5.250 1.2649 0.01195 0.00453 -0.1255 0.2911 0.0413
5.500 1.2887 0.01206 0.00485 -0.1250 0.2862 0.2423
5.750 1.3116 0.01099 0.00519 -0.1245 0.2840 1.0000
6.000 1.3368 0.01115 0.00535 -0.1242 0.2809 1.0000
6.250 1.3612 0.01136 0.00554 -0.1237 0.2779 1.0000
6.500 1.3847 0.01160 0.00576 -0.1231 0.2746 1.0000
6.750 1.4068 0.01191 0.00605 -0.1223 0.2707 1.0000
7.000 1.4310 0.01210 0.00625 -0.1218 0.2688 1.0000
7.250 1.4551 0.01227 0.00646 -0.1213 0.2667 1.0000
7.500 1.4784 0.01247 0.00667 -0.1207 0.2641 1.0000
7.750 1.5005 0.01271 0.00692 -0.1199 0.2616 1.0000
8.000 1.5206 0.01299 0.00720 -0.1187 0.2584 1.0000
8.250 1.5392 0.01334 0.00754 -0.1172 0.2539 1.0000
8.500 1.5623 0.01350 0.00774 -0.1166 0.2511 1.0000
8.750 1.5836 0.01374 0.00800 -0.1157 0.2478 1.0000
9.000 1.6035 0.01405 0.00832 -0.1146 0.2442 1.0000
9.250 1.6216 0.01445 0.00872 -0.1132 0.2405 1.0000
9.500 1.6421 0.01474 0.00905 -0.1123 0.2375 1.0000
9.750 1.6631 0.01501 0.00935 -0.1115 0.2340 1.0000
10.000 1.6821 0.01538 0.00974 -0.1103 0.2295 1.0000
10.250 1.6988 0.01587 0.01021 -0.1089 0.2238 1.0000
10.500 1.7191 0.01618 0.01057 -0.1080 0.2191 1.0000
10.750 1.7360 0.01669 0.01107 -0.1067 0.2127 1.0000
11.000 1.7530 0.01719 0.01159 -0.1054 0.2069 1.0000
11.250 1.7693 0.01774 0.01215 -0.1041 0.1997 1.0000
11.500 1.7838 0.01841 0.01280 -0.1026 0.1909 1.0000
11.750 1.7949 0.01931 0.01364 -0.1007 0.1768 1.0000
12.000 1.7993 0.02066 0.01486 -0.0981 0.1557 1.0000
12.250 1.7989 0.02240 0.01646 -0.0951 0.1326 1.0000
12.500 1.7993 0.02418 0.01815 -0.0924 0.1160 1.0000
12.750 1.8011 0.02593 0.01985 -0.0900 0.1023 1.0000
13.000 1.7988 0.02809 0.02191 -0.0875 0.0845 1.0000
13.250 1.7836 0.03137 0.02500 -0.0841 0.0568 1.0000
13.500 1.7710 0.03462 0.02816 -0.0812 0.0396 1.0000
13.750 1.7644 0.03745 0.03098 -0.0792 0.0299 1.0000
14.000 1.7622 0.04001 0.03356 -0.0776 0.0250 1.0000
14.250 1.7613 0.04254 0.03613 -0.0763 0.0221 1.0000
14.500 1.7614 0.04502 0.03867 -0.0751 0.0205 1.0000
14.750 1.7587 0.04787 0.04159 -0.0740 0.0189 1.0000
15.000 1.7599 0.05041 0.04420 -0.0732 0.0182 1.0000
15.250 1.7595 0.05317 0.04705 -0.0725 0.0174 1.0000
15.500 1.7569 0.05625 0.05021 -0.0719 0.0168 1.0000
15.750 1.7519 0.05971 0.05375 -0.0714 0.0162 1.0000
16.000 1.7435 0.06372 0.05786 -0.0710 0.0156 1.0000
16.250 1.7371 0.06758 0.06183 -0.0709 0.0152 1.0000
16.500 1.7322 0.07128 0.06563 -0.0709 0.0150 1.0000
16.750 1.7256 0.07529 0.06975 -0.0710 0.0147 1.0000
17.000 1.7174 0.07962 0.07418 -0.0713 0.0144 1.0000
17.250 1.7076 0.08425 0.07892 -0.0718 0.0141 1.0000
17.500 1.6958 0.08920 0.08398 -0.0724 0.0139 1.0000
17.750 1.6824 0.09448 0.08938 -0.0733 0.0137 1.0000
18.000 1.6679 0.10003 0.09504 -0.0744 0.0135 1.0000
18.250 1.6521 0.10590 0.10103 -0.0757 0.0133 1.0000
18.500 1.6349 0.11204 0.10729 -0.0773 0.0131 1.0000
18.750 1.6177 0.11830 0.11366 -0.0791 0.0129 1.0000
19.000 1.5995 0.12484 0.12031 -0.0812 0.0128 1.0000
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Polar data table (+)
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