GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 499 AIRFOIL (goe499-il) Reynolds number: 500,000 Max Cl/Cd: 149.41 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe499-il-500000.txt Download as CSV file: xf-goe499-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 499 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3395 0.14044 0.13810 -0.0350 1.0000 0.0154
-11.750 -0.3410 0.13849 0.13618 -0.0343 1.0000 0.0156
-11.500 -0.3466 0.13699 0.13471 -0.0334 1.0000 0.0158
-11.250 -0.3454 0.13447 0.13222 -0.0343 0.9996 0.0158
-11.000 -0.3341 0.13064 0.12839 -0.0386 0.9982 0.0159
-10.750 -0.3216 0.12663 0.12438 -0.0424 0.9968 0.0160
-10.500 -0.3088 0.12092 0.11866 -0.0431 0.9959 0.0164
-10.250 -0.2938 0.11736 0.11509 -0.0457 0.9947 0.0167
-10.000 -0.2801 0.11399 0.11171 -0.0483 0.9930 0.0171
-9.750 -0.2662 0.11055 0.10827 -0.0513 0.9908 0.0178
-9.500 -0.2518 0.10704 0.10475 -0.0546 0.9887 0.0187
-9.250 -0.2368 0.10334 0.10104 -0.0584 0.9868 0.0193
-9.000 -0.2199 0.09960 0.09729 -0.0651 0.9846 0.0212
-8.500 -0.0921 0.07038 0.06815 -0.0856 0.9716 0.0226
-8.250 -0.0744 0.06707 0.06484 -0.0877 0.9708 0.0234
-8.000 -0.0618 0.06390 0.06166 -0.0898 0.9673 0.0243
-7.750 -0.0493 0.06047 0.05822 -0.0925 0.9635 0.0256
-7.500 -0.0354 0.05657 0.05431 -0.0969 0.9602 0.0283
-7.250 -0.0200 0.05305 0.05077 -0.1034 0.9556 0.0297
-7.000 -0.0129 0.04991 0.04761 -0.1057 0.9474 0.0299
-6.750 0.0020 0.04554 0.04322 -0.1106 0.9428 0.0300
-6.500 0.0104 0.04176 0.03942 -0.1138 0.9348 0.0300
-6.250 0.0143 0.03481 0.03245 -0.1185 0.9291 0.0315
-6.000 0.0274 0.03295 0.03057 -0.1191 0.9223 0.0325
-5.750 0.0457 0.03050 0.02808 -0.1217 0.9171 0.0340
-5.500 0.0660 0.02744 0.02498 -0.1262 0.9117 0.0371
-5.250 0.1157 0.01359 0.01070 -0.1542 0.9066 0.0428
-5.000 0.1382 0.01276 0.00986 -0.1543 0.9026 0.0442
-4.750 0.1643 0.01143 0.00843 -0.1563 0.8988 0.0464
-4.500 0.2044 0.00711 0.00347 -0.1654 0.8953 0.0565
-4.250 0.2287 0.00677 0.00318 -0.1653 0.8913 0.0590
-4.000 0.2851 0.01472 0.00968 -0.1798 0.8996 0.0427
-3.750 0.3122 0.01443 0.00929 -0.1796 0.8948 0.0418
-3.250 0.3704 0.01225 0.00674 -0.1804 0.8875 0.0409
-3.000 0.3983 0.01129 0.00563 -0.1805 0.8834 0.0406
-2.750 0.4262 0.01067 0.00492 -0.1805 0.8791 0.0407
-2.500 0.4548 0.01021 0.00436 -0.1806 0.8752 0.0411
-2.250 0.4831 0.00984 0.00392 -0.1806 0.8712 0.0415
-2.000 0.5105 0.00934 0.00337 -0.1805 0.8659 0.0422
-1.750 0.5389 0.00899 0.00297 -0.1806 0.8615 0.0430
-1.500 0.5678 0.00876 0.00268 -0.1807 0.8583 0.0440
-1.250 0.5951 0.00859 0.00250 -0.1806 0.8538 0.0463
-1.000 0.6231 0.00845 0.00234 -0.1805 0.8496 0.0483
-0.750 0.6515 0.00834 0.00219 -0.1805 0.8458 0.0513
-0.500 0.6794 0.00813 0.00212 -0.1805 0.8415 0.0954
-0.250 0.7070 0.00788 0.00215 -0.1806 0.8364 0.1902
0.000 0.7350 0.00779 0.00214 -0.1805 0.8316 0.2327
0.250 0.7619 0.00771 0.00216 -0.1803 0.8252 0.2698
0.500 0.7892 0.00762 0.00215 -0.1801 0.8188 0.3042
0.750 0.8166 0.00747 0.00220 -0.1801 0.8130 0.3740
1.000 0.8433 0.00726 0.00234 -0.1799 0.8062 0.5198
1.250 0.8698 0.00706 0.00242 -0.1795 0.7993 0.6329
1.500 0.8931 0.00643 0.00241 -0.1783 0.7905 1.0000
1.750 0.9197 0.00647 0.00242 -0.1779 0.7805 1.0000
2.000 0.9458 0.00650 0.00241 -0.1773 0.7662 1.0000
2.250 0.9708 0.00656 0.00237 -0.1764 0.7441 1.0000
2.500 0.9951 0.00666 0.00239 -0.1755 0.7137 1.0000
2.750 1.0180 0.00688 0.00244 -0.1743 0.6723 1.0000
3.000 1.0348 0.00752 0.00263 -0.1719 0.5898 1.0000
3.250 1.0511 0.00833 0.00301 -0.1696 0.5161 1.0000
3.500 1.0691 0.00907 0.00340 -0.1678 0.4543 1.0000
3.750 1.0847 0.01004 0.00388 -0.1656 0.3610 1.0000
4.000 1.0811 0.01311 0.00535 -0.1607 0.0603 1.0000
4.250 1.1014 0.01388 0.00597 -0.1592 0.0258 1.0000
4.500 1.1242 0.01436 0.00649 -0.1582 0.0223 1.0000
4.750 1.1456 0.01498 0.00718 -0.1569 0.0200 1.0000
5.000 1.1641 0.01590 0.00822 -0.1551 0.0186 1.0000
5.250 1.1845 0.01655 0.00893 -0.1537 0.0181 1.0000
5.500 1.2031 0.01735 0.00980 -0.1519 0.0175 1.0000
5.750 1.2216 0.01811 0.01061 -0.1502 0.0164 1.0000
6.000 1.2387 0.01898 0.01152 -0.1483 0.0155 1.0000
6.250 1.2543 0.02000 0.01262 -0.1461 0.0150 1.0000
6.500 1.2694 0.02114 0.01380 -0.1438 0.0146 1.0000
6.750 1.2845 0.02239 0.01510 -0.1416 0.0142 1.0000
7.000 1.3026 0.02392 0.01667 -0.1399 0.0139 1.0000
7.250 1.3305 0.02605 0.01893 -0.1395 0.0146 1.0000
7.500 1.3881 0.03172 0.02502 -0.1419 0.0244 1.0000
7.750 1.4094 0.03316 0.02662 -0.1407 0.0224 1.0000
8.000 1.4311 0.03512 0.02865 -0.1399 0.0210 1.0000
8.250 1.4084 0.03633 0.03056 -0.1329 0.0186 1.0000
8.500 1.4190 0.03510 0.02958 -0.1295 0.0178 1.0000
8.750 1.4312 0.03643 0.03114 -0.1268 0.0165 1.0000
9.000 1.4401 0.03922 0.03416 -0.1241 0.0155 1.0000
9.250 1.4455 0.04235 0.03750 -0.1212 0.0148 1.0000
9.500 1.4478 0.04566 0.04101 -0.1181 0.0144 1.0000
9.750 1.4476 0.04908 0.04461 -0.1150 0.0140 1.0000
10.000 1.4446 0.05256 0.04824 -0.1116 0.0138 1.0000
10.250 1.4339 0.05582 0.05166 -0.1071 0.0136 1.0000
10.500 1.4243 0.05948 0.05545 -0.1034 0.0135 1.0000
10.750 1.4092 0.06371 0.05983 -0.0996 0.0133 1.0000
11.000 1.3871 0.06846 0.06477 -0.0958 0.0132 1.0000
11.250 1.3635 0.07327 0.06978 -0.0925 0.0131 1.0000
11.500 1.3362 0.07891 0.07561 -0.0899 0.0131 1.0000
11.750 1.3117 0.08289 0.07980 -0.0879 0.0132 1.0000
12.000 1.2774 0.08920 0.08630 -0.0869 0.0131 1.0000
12.250 1.2356 0.09378 0.09110 -0.0862 0.0132 1.0000
12.500 1.1872 0.10054 0.09820 -0.0883 0.0136 1.0000
12.750 1.1649 0.10645 0.10423 -0.0906 0.0135 1.0000
13.000 1.1153 0.11773 0.11582 -0.0977 0.0140 1.0000
13.250 1.0789 0.12884 0.12712 -0.1051 0.0142 1.0000
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