GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Reynolds number: 500,000 Max Cl/Cd: 104.53 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe329-il-500000.txt Download as CSV file: xf-goe329-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2664 0.10969 0.10744 -0.0346 1.0000 0.0190
-9.500 -0.2610 0.10689 0.10466 -0.0356 1.0000 0.0195
-9.250 -0.2576 0.10427 0.10208 -0.0362 1.0000 0.0200
-9.000 -0.2513 0.10135 0.09918 -0.0380 0.9977 0.0206
-8.750 -0.1308 0.08083 0.07867 -0.0596 0.9405 0.0214
-8.500 -0.1226 0.07769 0.07551 -0.0589 0.9288 0.0215
-8.250 -0.1168 0.07477 0.07255 -0.0588 0.9176 0.0217
-8.000 -0.1984 0.08467 0.08244 -0.0593 0.9440 0.0214
-7.750 -0.1888 0.08185 0.07959 -0.0589 0.9314 0.0216
-7.500 -0.1799 0.07914 0.07684 -0.0598 0.9191 0.0217
-7.250 -0.1692 0.07629 0.07394 -0.0619 0.9081 0.0220
-7.000 -0.1567 0.07331 0.07091 -0.0647 0.8976 0.0223
-6.750 -0.1420 0.07017 0.06773 -0.0682 0.8879 0.0228
-6.500 -0.1254 0.06692 0.06440 -0.0720 0.8794 0.0234
-6.250 -0.1048 0.06327 0.06070 -0.0771 0.8705 0.0244
-6.000 -0.0647 0.05754 0.05471 -0.0897 0.8626 0.0253
-5.750 -0.0370 0.05327 0.05027 -0.0947 0.8547 0.0254
-5.500 -0.0234 0.04963 0.04659 -0.0953 0.8480 0.0256
-5.250 -0.0048 0.04714 0.04407 -0.0962 0.8404 0.0258
-5.000 0.0161 0.04483 0.04169 -0.0974 0.8333 0.0262
-4.750 0.0398 0.04245 0.03923 -0.0991 0.8258 0.0267
-4.500 0.0659 0.03989 0.03653 -0.1010 0.8185 0.0275
-4.250 0.0943 0.03714 0.03363 -0.1031 0.8113 0.0286
-4.000 0.1371 0.03375 0.02968 -0.1058 0.8042 0.0303
-3.750 0.1597 0.03010 0.02594 -0.1071 0.7969 0.0307
-3.500 0.1844 0.02834 0.02412 -0.1079 0.7882 0.0311
-3.250 0.2105 0.02678 0.02244 -0.1086 0.7798 0.0317
-3.000 0.2379 0.02527 0.02079 -0.1092 0.7709 0.0327
-2.750 0.2673 0.02365 0.01898 -0.1097 0.7617 0.0345
-2.500 0.3002 0.02154 0.01631 -0.1100 0.7525 0.0368
-2.250 0.3269 0.02001 0.01475 -0.1106 0.7408 0.0376
-2.000 0.3545 0.01898 0.01363 -0.1111 0.7286 0.0388
-1.750 0.3833 0.01808 0.01255 -0.1113 0.7157 0.0412
-1.500 0.4132 0.01693 0.01103 -0.1114 0.7015 0.0451
-1.250 0.4407 0.01608 0.01011 -0.1117 0.6844 0.0468
-1.000 0.4689 0.01570 0.00954 -0.1117 0.6647 0.0507
-0.750 0.4969 0.01485 0.00846 -0.1119 0.6435 0.0560
-0.500 0.5244 0.01463 0.00810 -0.1119 0.6199 0.0614
0.000 0.5794 0.01370 0.00677 -0.1121 0.5734 0.0798
0.250 0.6063 0.01349 0.00646 -0.1121 0.5516 0.0881
0.750 0.6644 0.01207 0.00455 -0.1110 0.5164 0.0498
1.000 0.6923 0.01193 0.00422 -0.1107 0.5016 0.0441
1.250 0.7197 0.01172 0.00395 -0.1107 0.4884 0.0433
1.500 0.7474 0.01159 0.00376 -0.1107 0.4764 0.0440
1.750 0.7751 0.01144 0.00359 -0.1107 0.4657 0.0435
2.000 0.8028 0.01135 0.00345 -0.1108 0.4558 0.0432
2.250 0.8306 0.01131 0.00337 -0.1109 0.4463 0.0433
2.500 0.8583 0.01132 0.00335 -0.1110 0.4381 0.0439
2.750 0.8860 0.01134 0.00332 -0.1110 0.4303 0.0458
3.000 0.9135 0.01143 0.00338 -0.1110 0.4233 0.0487
3.250 0.9410 0.01152 0.00346 -0.1111 0.4164 0.0559
3.500 0.9595 0.00994 0.00376 -0.1095 0.4107 1.0000
3.750 0.9872 0.01008 0.00386 -0.1096 0.4044 1.0000
4.000 1.0141 0.01030 0.00400 -0.1095 0.3984 1.0000
4.250 1.0411 0.01050 0.00417 -0.1095 0.3932 1.0000
4.500 1.0684 0.01067 0.00433 -0.1095 0.3879 1.0000
4.750 1.0950 0.01090 0.00452 -0.1095 0.3829 1.0000
5.000 1.1216 0.01114 0.00473 -0.1094 0.3782 1.0000
5.250 1.1487 0.01130 0.00492 -0.1094 0.3734 1.0000
5.500 1.1751 0.01153 0.00513 -0.1093 0.3688 1.0000
5.750 1.2010 0.01180 0.00537 -0.1092 0.3636 1.0000
6.000 1.2278 0.01193 0.00555 -0.1091 0.3572 1.0000
6.250 1.2530 0.01220 0.00577 -0.1089 0.3502 1.0000
6.500 1.2795 0.01233 0.00596 -0.1088 0.3430 1.0000
6.750 1.3046 0.01259 0.00619 -0.1085 0.3356 1.0000
7.000 1.3306 0.01276 0.00641 -0.1084 0.3284 1.0000
7.250 1.3552 0.01302 0.00665 -0.1081 0.3205 1.0000
7.500 1.3808 0.01321 0.00690 -0.1079 0.3135 1.0000
7.750 1.4048 0.01350 0.00717 -0.1074 0.3031 1.0000
8.000 1.4288 0.01377 0.00744 -0.1070 0.2903 1.0000
8.250 1.4519 0.01411 0.00774 -0.1065 0.2694 1.0000
8.500 1.4668 0.01509 0.00838 -0.1047 0.2109 1.0000
8.750 1.4506 0.01853 0.01084 -0.0986 0.0688 1.0000
9.000 1.4519 0.02026 0.01232 -0.0948 0.0309 1.0000
9.250 1.4625 0.02110 0.01322 -0.0921 0.0270 1.0000
9.500 1.4717 0.02208 0.01424 -0.0895 0.0246 1.0000
9.750 1.4796 0.02320 0.01545 -0.0868 0.0229 1.0000
10.000 1.4898 0.02421 0.01654 -0.0847 0.0219 1.0000
10.250 1.4982 0.02540 0.01783 -0.0826 0.0210 1.0000
10.500 1.5047 0.02679 0.01931 -0.0804 0.0202 1.0000
10.750 1.5078 0.02852 0.02113 -0.0782 0.0195 1.0000
11.000 1.5054 0.03081 0.02353 -0.0758 0.0189 1.0000
11.250 1.5008 0.03345 0.02630 -0.0736 0.0184 1.0000
11.500 1.5052 0.03542 0.02837 -0.0722 0.0181 1.0000
11.750 1.5070 0.03771 0.03077 -0.0710 0.0176 1.0000
12.000 1.5073 0.04026 0.03343 -0.0699 0.0172 1.0000
12.250 1.5056 0.04312 0.03639 -0.0689 0.0168 1.0000
12.500 1.5025 0.04626 0.03964 -0.0682 0.0164 1.0000
12.750 1.4980 0.04968 0.04316 -0.0676 0.0161 1.0000
13.000 1.4924 0.05335 0.04694 -0.0673 0.0159 1.0000
13.250 1.4862 0.05725 0.05093 -0.0671 0.0157 1.0000
13.500 1.4791 0.06135 0.05512 -0.0672 0.0154 1.0000
13.750 1.4714 0.06558 0.05945 -0.0673 0.0152 1.0000
14.000 1.4634 0.06985 0.06380 -0.0673 0.0150 1.0000
14.250 1.4549 0.07396 0.06797 -0.0671 0.0148 1.0000
14.500 1.4500 0.07738 0.07145 -0.0663 0.0146 1.0000
14.750 1.4510 0.08058 0.07475 -0.0665 0.0144 1.0000
15.000 1.4521 0.08368 0.07794 -0.0666 0.0143 1.0000
15.250 1.4532 0.08677 0.08112 -0.0667 0.0140 1.0000
15.500 1.4546 0.08981 0.08425 -0.0667 0.0138 1.0000
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